[Federal Register Volume 64, Number 129 (Wednesday, July 7, 1999)]
[Proposed Rules]
[Pages 36618-36623]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-16911]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-87-AD]
RIN 2120-AA64
Airworthiness Directives; Precise Flight, Inc. Model SVS III
Standby Vacuum Systems
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to all U.S. owners and operators of aircraft
equipped with Precise Flight, Inc. Model SVS III standby vacuum systems
installed in accordance with the applicable supplemental type
certificate (STC) or through field approval. The proposed AD would
require
[[Page 36619]]
incorporating revised operating limitations for the affected standby
vacuum systems into the airplane flight manual (AFM), and repetitively
inspecting the push-pull cable, vacuum lines, saddle fittings, and
shuttle valve for correct installation and damage (wear, chafing,
deterioration, etc.). The proposed AD would also require immediately
correcting any discrepancy found and conducting a function test of the
vacuum system after the inspections. This AD results from reports of
shuttle valve failure and standby vacuum system malfunction on
aircraft. The actions specified by the proposed AD are intended to
detect and correct problems with the standby vacuum system before
failure or malfunction and to provide operating procedures for the
pilot regarding the use and limitations of this system.
DATES: Comments must be received on or before August 30, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-CE-87-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106. Comments may be inspected at this location
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
Service information that applies to the proposed AD may be obtained
from Precise Flight, Inc., 63120 Powell Butte Road, Bend, Oregon 97701;
telephone: (800)-547-2558. This information also may be examined at the
Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Ms. Della Swartz, Aerospace Engineer,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW,
Renton, Washington 98055-4065; telephone: (425) 227-2596; facsimile:
(425) 227-1181.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 98-CE-87-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 98-CE-87-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
The FAA has received several reports of problems on aircraft
equipped with Precise Flight, Inc. Model SVS III standby vacuum
systems. In particular, the reports show 14 incidents of failed shuttle
control valves and 2 accidents where improper use of the standby vacuum
system was a factor. Other parts of the standby vacuum system that
could fail include the saddle fittings, vacuum lines, and the push-pull
cables.
The standby vacuum system is intended to provide emergency vacuum
power for aircraft instruments when the primary vacuum system fails.
The design of the Precise Flight, Inc. Model SVS III standby vacuum
system is such that it may not be able to provide sufficient power to
maintain altitude and operate the vacuum instruments.
Failure of the standby vacuum system in instrument flight rules
(IFR) can lead to the pilot making incorrect decisions based on the
data received from the instruments with consequent loss of control of
the aircraft.
The Precise Flight, Inc. Model SVS III standby vacuum systems are
installed on aircraft through a supplemental type certificate (STC) or
through field approval. The Applicability section of the proposed AD
lists the applicable STC's and aircraft that could have these standby
vacuum systems installed. This list is not meant to be exhaustive nor
does it include all aircraft with the systems installed through field
approval.
Relevant Service Information
Precise Flight, Inc. has issued the following:
--Airplane Flight Manual Supplements (AFMS) for Standby Vacuum Systems
(each document corresponds with the Applicable STC), which include
operating procedures for the pilot regarding the use and limitations of
the Model SVS III standby vacuum system; and
--Precise Flight Instructions for Continued Airworthiness (Section 3.3
of Installation Report No. 50050), Revision 25, dated August 26, 1996,
which specifies procedures for inspecting the push-pull cables, vacuum
lines, saddle fittings, and shuttle valve for correct installation and
damage (wear, chafing, deterioration, etc.); immediately correcting any
discrepancy found; and conducting a function test of the vacuum system
after each inspection.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, including the
above-referenced service information, the FAA has determined that AD
action should be taken to detect and correct problems with the standby
vacuum system before failure or malfunction and to provide operating
procedures for the pilot regarding the use and limitations of this
system.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in aircraft equipped with Precise Flight, Inc. Model
SVC III standby vacuum systems, the FAA is proposing AD action. The
proposed AD would require incorporating revised operating limitations
for the affected standby vacuum systems into the airplane flight manual
(AFM), and repetitively inspecting the push-pull cable, vacuum lines,
saddle fittings, and shuttle valve for correct installation and damage
(wear, chafing, deterioration, etc.). The proposed AD would also
require immediately correcting any discrepancy found and conducting a
function test of the vacuum system after each inspection.
Compliance Time of the Proposed AD
The compliance times of the proposed AD are presented in calendar
time. Although malfunction or failure of the standby vacuum systems is
only unsafe while the aircraft is in flight, the condition is not a
direct result of repetitive aircraft operation. The unsafe
[[Page 36620]]
condition could exist on a standby vacuum system installed on an
aircraft with only 50 hours time-in-service (TIS), but may not develop
on another standby vacuum system installed on an aircraft until 1,000
hours TIS. The inspection compliance times are proposed to coincide
with annual inspections so as to allow the owner/operator of the
aircraft to have the proposed action accomplished at a time when he/she
had already scheduled maintenance activities.
Cost Impact
The FAA estimates that 10,000 standby vacuum systems would be
affected by the proposed AD, that it would take approximately 3
workhours per vacuum system to accomplish the proposed actions, and
that the average labor rate is approximately $60 an hour. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $1,800,000, or $180 per airplane.
These figures only take into account the costs of the initial
inspection and initial functional test of the standby vacuum systems;
subsequent inspections and functional tests and any corrective actions
are not included in the cost impact. The FAA has no way of determining
the number of repetitive inspections and functional tests each airplane
owner/operator will incur over the life of an airplane incorporating
one of the affected standby vacuum systems. The FAA also has no way of
determining the number of standby vacuum systems that would require
corrective action based on the inspection results.
Regulatory Impact
The regulations proposed herein would not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated,
will not have a significant economic impact, positive or negative, on a
substantial number of small entities under the criteria of the
Regulatory Flexibility Act. A copy of the draft regulatory evaluation
prepared for this action has been placed in the Rules Docket. A copy of
it may be obtained by contacting the Rules Docket at the location
provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Precise Flight, Inc.: Docket No. 98-CE-87-AD.
Applicability: Model SVS III standby vacuum systems, installed
on, but not limited to, the aircraft listed in the following chart.
These systems can be installed either in accordance with the
applicable supplemental type certificate (STC) or through field
approval:
------------------------------------------------------------------------
Affected STC Make and model airplanes
------------------------------------------------------------------------
SA2160NM............................. Raytheon Beech Models 23, A23,
A23A, A23-19, 19A, B19, B19A,
A23-24, B23, C23, A24, A24R,
B24R, C24R, 35, A35, B35, C35,
D35, E35, F35, G35, 35R, H35,
J35, K35, M35, N35, P35, S35,
V35, V35A, V35B, 35-33, 35-A33,
35-B33, 35-C33, 35-C33A, E33,
E33A, E33C, F33, F33A, F33C,
G33, 36, A36, A36TC, B36TC,
4S(YT-34), A45(T-34A, B-45),
D45(T-34B), and 77 Series.
SA2161NM............................. Raytheon Beech Model V35B.
SA2162NM............................. Cessna Models 120, 140, 140A,
150, 150A, 150B, 150C, 150D,
150E, 150F, 150G, 150H, 150J,
150K, 150L, A150L, 150M, 152,
A152, A150K, A150M, 170, 170A,
170B, 172, 172A, 172B, 172C,
172D, 172E, 172F (USAFT-41A),
172G, 172H(USAFT-41A), 172I,
172K, 172L, 172M, 172N, 172P,
172Q, 175, 175A, 175B, 175C,
P172D, R172E (USAFT-41B, USAFT41-
3, and USAFT-41D), R172F (USAFT-
41D and USAFT-41C), R172G (USAFT-
41D), R172H (USAFT-41D), R172J,
R172K, 172RG, 177, 177A, 177B,
177RG, 180, 180A, 180B, 180C,
180D, 180E, 180F, 180G, 180H,
180J, 180K, 182, 182A, 182B,
182C, 182D, 182E, 182F, 182G,
182H, 182J, 182K, 182L, 182M,
182N, 182P, 182Q, 182R, 182RG,
T182, T182RG, T182R, 185, 185A,
185B, 185C, 185D, 185E, A185E,
A185F, 188, 188A, 188B, A188,
A188B, T188C, 206, P206, P206A,
P206B, P206C, P206D, P206E,
TP206A, TP206B, TP206C, TP206D.
TP206E, U206-A, U206-B, U206-C,
U206-D, U206-E, U206-F, U206-G,
TU206-A, TU206-B, TU206-C, TU206-
D, TU206-E, TU206-F, TU206-G,
207, 207A, T207, T207A, 210,
210A, 210B, 210C, 210D, 210E,
210F, 210-5 (205), 210-5A
(205A), T210F, 210G, T-210G,
210H, T-210H, 210J, 205P, T-
210J, 210K, T-210K, T210L, 210L,
210M, T210M, 210N, P210N, T210N,
205T, 210R, P210R, 205U, T210R,
210-5, 210-5A, 305A (USAF 0-1A),
305C (USAF 0-1E), 305D (USAF 0-
1F), 305F, 305B (USAF T0-1D),
305E (0-1D or 0-1F), and 321
(Navy 0E-2).
SA2163NM............................. Cessna Model U206G.
SA2164NM............................. Cessna Model 180Q.
SA2166NM............................. Cessna Model 177.
SA2167NM............................. The New Piper Aircraft, Inc.
(Piper) Models L-14, PA-12, PA-
12S, PA-14, PA-15, PA-16, PA-
16S, PA-17, PA-18, PA-18A, PA-
18S, PA-18-105 (Special), PA-18S-
105(SP), PA-18-125 (Army L-21A),
PA-18AS-125, PA-18S-125, PA-18-
135, PA-18A-135, PA-18AS-135, PA-
18S-135, PA-18-150, PA-18A-150,
PA-18AS-150, PA-18S-150, PA-19
(Army L-18C), PA-19S, PA-20, PA-
20S, PA-20-115, PA-20S-115, PA-
20-135, PA-22, PA-22-108, PA-22-
135, PA-22S-135, PA-22-150, PA-
22S-150, PA-22-160, PA-22S-160,
PA-24, PA-24-250, PA-24-260, PA-
24-400, PA-25, PA-25-235, PA-25-
260, PA-32-260, PA-32RT-300, PA-
32RT-301T, PA-32-300, PA-32RT-
300T, PA-32-301, PA-32S-300, PA-
32R-301, PA-32-301T, PA-32R-300,
PA-32R-301T, PA-28-140, PA-28-
141, PA-28-150, PA-28-151, PA-28-
160, PA-28S-160, PA-28-180, PA-
28R-180, PA-28S-180, PA-28-235,
PA-28S-235, PA-28-181, PA-28-
161, PA-28R-200, PA-28R-201, PA-
28R-201T, PA-28-236, PA-28RT-
201, PA-28RT-201T, PA-28-201T,
PA-36-285, PA-36-300, PA-36-375,
PA-38-112, and PA-46-31OP.
SA2168NM............................. Mooney Models M20, M20A, M20B,
M20C, M20D, M20E, M20F, M20G,
M20J, M20K, M20M , and M22.
SA2683NM............................. Aerocar, Inc. Model I.
[[Page 36621]]
Aerodifusion, S.L. Model Jodel D-
1190S.
Aeromere, S.A. Model Falco F.8.L.
Aeronautica Macchi S.P.A. Models
AL60, AL60-B, AL60-F5, and AL60-
C5.
Aeronautica Macchi & Aerfer Model
AM-3.
Aeronca Inc. Models 15AC and
S15AC.
Aerospatiale Model TB20 Trinidad.
Arctic Aircraft Co., Inc. Models
S-1A, S-1A-65F, S-1A-85F, S-1A-
90F, S-1B1(Army L-67 XL-6), and
S-1B2.
Avions Mudry et Cie Model CAP
10B.
American Champion Models
(Bellanca, Aeronca) 7AC, 7ACA,
S7AC (L-16A), 7BCM (L-16B),
7CCM, 7DC, S7DC, 7EC, S7EC,
7ECA, 7FC, 7GC, 7GCA, 7GCCA,
7GCB, 7GCBA, 7GCBC, 7HC, 7JC,
7KC, 7KCAB, 8KCAB, 8GCBC, 11AC,
S11AC, 11BC, S11BC, 11CC, and
S11CC.
Bellanca Aircraft Corporation
Models 14-9, 14-9L, 14-12F-3, 14-
13, 14-13-2, 14-13-3, 14-13-3W,
14-19, 14-19-2, 14-19-3A, 17-30,
17-31, 17-31TC, 17-30A, 17-31A,
and 17-31ATC.
Biemond, C. Model Teal CB1.
Board, G.R. Models Columbia XJL-1
and Bolkow Jr.
Clark Aircraft, Inc. Models 12
and 1000.
Falcon Aircraft Corporation Model
F-1.
Flug und Fahrzeugwerke AG Model
AS 202/15 ``Brand''.
Found Brothers Model FBA-2C
Fuji Heavy Industries Models FA-
200-160, FA-200-180, and FA-200-
180AO.
Funk Aircraft Model Funk C.
Kearns, Edward Scott (Garcia,
Henry S.) Model (Emigh) Trojan A-
2.
Swift Museum Foundation, Inc.
Model (Globe) GC-1A, GC-1B.
Goodyear Aircraft Model GA-22A.
Great Lakes Aircraft Model 2T-1A-
1 and 2T-1A-2.
Grumman American Models G-164, G-
164A, G-164B, AA-1, AA-1A, AA-
1B, AA-1C, AA-5, AA-5A, and AA-
5B.
Commander Aircraft (Gulfstream)
Models 112, (112A, 112B, 112TC,
112TCA, 114, and 114A.
Helio Enterprises Models H-250, H-
295 (USAF U-10D), H-391 (USAF YL-
24), H-395 (SAF L-28A), H-395A,
HT-295, and H-700.
Prop-Jets, Inc. (Interceptor
Corp., Aero Commander, Meyers)
Models 200, 200A, 200B, 200C,
and 200D.
C. Itoh Aircraft Maintenance &
Engineering Co. LTD. Model N-62.
Jamieson Corporation Model J-2-
L1B.
Jodel, Avion Models D-140-B, DR-
1050, D-1190, and 150.
Lake Models C-1, C-2-IV, LA-4, LA-
4-200, and LA-4-250.
Luscombe Aircraft Corp. Models 8,
8A, 8B, 8C, 8D, 8E, 8F, T-8F,
and 11A.
Maule Aerospace Technology Corp.
Models Bee Dee M-4, M-4, M-4C, M-
4S, M-4T, M-4-180C, M-4-180S, M-
4-210, M-4-201C, M-4-210S, M-4-
210T, M-4-220S, M-4-220T, M-5-
180C, M-5-200, M-5-210C, M-5-
210TC, M-T-220C, M-5-235, M-5-
235C, M-6-180, M-6-235, M-7-235,
MX-7-180, MX-7-235.
Messerschmitt-Bolkow Models BO-
209-150.
FV&RV, BO209-160 FV&RV, BO-209,
and 150OFF.
Nardi S.A. Model FN-333.
Jimmie Thompson Enterprise
(Navion Rangemaster Aircraft
Corporation) Models Navion (L-
17A).
Navion A (L-17B, L-17C), Navion
B, D, E, F, G, and H.
White International Ltd. Models
(Pitts) S-1S, S-1T, S-2, and S-
2A.
Procaer S.P.A. Models F 15/B, F
15/C, and F 15/E.
Gulfstream Aerospace Corporation
(Rockwell) Models 111, 112,
112B, 112TC, 112TCA, and 114.
Aermacchi S.p.A Models S.205,
S.205-18F, S.205-18/R, S.205-20/
F, S.205-20/R, S.205-22/R,
S.208, S.208A, F.260, and
F.260B.
Socata Groupe Aerospatiale Models
Rallye Series MS880B, MS885,
MS892-A-150, MS892E-150, MS893A,
MS893E, MS894A, MS894E,
TB9,TB10, and TB21.
Stinson Models 108-2 and 108-3.
Sud Aviation Models Gardan GY.80-
1500, GY.80-160, and GY.80-180.
Taylorcraft Aircraft Company
Models F19, F21, and F21A.
Univair Aircraft Corporation
(Forney) Models F-1, F-1A,
(ERCO)E, 415D, (ALON)A-2, A20a,
(Mooney)M10, (Mooney) (ERCO) 415-
C, and 415-CD.
Augustair, Inc. (Varga Aircraft
Corporation) Models 2150, 2150A,
and 2180.
------------------------------------------------------------------------
Note 1: The above list includes the aircraft where the Precise
Flight, Inc. Model SVS III standby vacuum systems could be installed
through STC. This list is not meant to be exhaustive nor does it
include all aircraft with the systems installed through field
approval.
Note 2: This AD applies to any aircraft with a standby vacuum
system installed that is identified in the preceding applicability
provision, regardless of whether it has been modified, altered, or
repaired in the area subject to the requirements of this AD. For
aircraft that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the owner/
operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD;
and, if the unsafe condition has not been eliminated, the request
should include specific proposed actions to address it.
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To detect and correct problems with the standby vacuum system
before failure or malfunction and to provide operating procedures
for the pilot regarding the use and limitations of this system,
accomplish the following:
(a) Within the next 30 calendar days after the effective date of
this AD, accomplish whichever (paragraph (a)(1) or (a)(2) below) of
the following that applies:
(1) For airplanes with the affected standby vacuum system
installed in accordance with the applicable STC, incorporate the
applicable Precise Flight, Inc. Airplane Flight Manual Supplement
(AFMS) for Standby Vacuum Systems (each document corresponds with
the applicable STC as
[[Page 36622]]
presented in the chart below) into the Airplane Flight Manual (AFM),
including installing all placards specified in these AFMS's; or
insert a copy of the Appendix to this AD into the AFM, including
installing all placards specified in the Appendix:
------------------------------------------------------------------------
Applicable STC AFMS Date
------------------------------------------------------------------------
SA2160NM............................ May 7, 1998.
SA2161NM............................ August 6, 1998.
SA2162NM............................ August 6, 1998.
SA2163NM............................ August 6, 1998.
SA2164NM............................ August 6, 1998.
SA2166M............................. August 6, 1998.
SA2167NM............................ August 6, 1998.
SA2168NM............................ August 6, 1998.
SA2683NM............................ August 6, 1998; or.
------------------------------------------------------------------------
(2) For airplanes with the affected standby vacuum system
installed through field approval, insert the Appendix to this AD
into the AFM, including installing all placards specified in the
Appendix.
(b) Within the next 12 calendar months after the effective date
of this AD, and thereafter at intervals specified in the following
paragraphs, inspect the push-pull cable, vacuum lines, saddle
fittings, and shuttle valve for correct installation and damage
(wear, chafing, deterioration, etc.). Accomplish these inspections
in accordance with Precise Flight Instructions for Continued
Airworthiness (Section 3.3 of Installation Report No. 50050),
Revision 25, dated August 26, 1996.
(1) Reinspect the push-pull cable, vacuum lines, and saddle
fittings at intervals not to exceed 12 calendar months; and
(2) Reinspect the shuttle valve at intervals not to exceed 24
calendar months.
(c) Prior to further flight after each inspection required by
paragraph (b) of this AD, accomplish the following in accordance
with Precise Flight Instructions for Continued Airworthiness
(Section 3.3 of Installation Report No. 50050), Revision 25, dated
August 26, 1996.
(1) Correct any discrepancy found; and
(2) Conduct a function test of the vacuum system and assure
proper function.
(d) Special flight permits may be issued in accordance with
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to a location where the
requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue, SW, Renton, Washington
98055-4065. The request shall be forwarded through an appropriate
FAA Maintenance Inspector, who may add comments and then send it to
the Manager, Seattle ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(f) All persons affected by this directive may obtain copies of
the documents referred to herein upon request to Precise Flight,
Inc., 63120 Powell Butte Road, Bend, Oregon 97701; or may examine
this/these document(s) at the FAA, Central Region, Office of the
Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
BILLING CODE 4910-13-U
Appendix to Docket No. 98-CE-87-AD
System Description
A Precise Flight Standby Vacuum System may be installed to
provide a temporary vacuum system in the event of a primary vacuum
failure. The Standby Vacuum System operates on the differential
between the intake manifold and ambient air pressure and is directed
through a shuttle valve system to drive your flight instruments.
I. Operating Limitations
A. Instructions
1. The Standby Vacuum System is for emergency or standby use
only and not for dispatch purposes.
2. Vacuum powered add/or Vacuum gyro directed autopilot
operation may be unreliable when the Standby Vacuum System is the
sole source of vacuum. Vacuum powered or vacuum gyro directed
autopilot should be OFF when operating with a failed primary vacuum
system.
3. The Supplemental Vacuum System is not designed to operate
pneumatic de-ice systems. DO NOT operate a pneumatic de-ice system
when operating with a failed primary vacuum system.
4. Above 10,000 ft. pressure altitude, engine power settings may
have to be significantly reduced to provide adequate vacuum power
for proper gyro instrument operation.
5. The following placards are required to be in full view of
pilot:
B. Placards
Placard to be located on the push/pull control cable.
Placard to be located around the LED for the pump inop warning
light.
Placard to be placed in front and in full view of the pilot.
------------------------------------------------------------------------
-------------------------------------------------------------------------
STANDBY VACUUM SYSTEM EQUIPPED: FOR OPERATING INSTRUCTIONS AND
LIMITATIONS SEE SUPPLEMENT IN OWNERS MANUAL OR PILOTS OPERATING
HANDBOOK
------------------------------------------------------------------------
One of the following placards must be placed in full view of the
pilot near the instrument vacuum indicator after appropriate entries
have been made.
Approximate Standby Vacuum Available--Altitude-Power Chart for Aircraft With Constant Speed Propeller--Maximum
Continuous RPM.
----------------------------------------------------------------------------------------------------------------
Press alt. (Ft.) RPM Man. pressure SVS vacuum in Hg. Min.
----------------------------------------------------------------------------------------------------------------
2000................................. Max. Cont..............
4000................................. Max. Cont..............
6000................................. Max. Cont..............
8000................................. Max. Cont..............
10,000............................... Max. Cont..............
----------------------------------------------------------------------------------------------------------------
Approximate Standby Vacuum Available--Altitude-Power Chart for aircraft
With a Fixed Pitch Propeller
------------------------------------------------------------------------
SVS vacuum in Hg
Press alt. (Ft.) RPM min.
------------------------------------------------------------------------
2000............................
4000............................
6000............................
8000............................
10,000..........................
------------------------------------------------------------------------
II. Operating Procedures
A. Normal Procedures
1. Ground Check
a. Cycle the Standby Vacuum Control Knob Out--ON--, and return
Control Knob IN--OFF--position.
2. Before Takeoff
a. Idle Engine at low speed, momentarily pull the standby vacuum
knob out--ON--and check vacuum gauge. Normally, the vacuum reading
will be slightly higher. After checking system push Standby Vacuum
System knob IN--OFF--. Check that vacuum gauge has returned to the
previous reading.
3. Enroute
a. Regularly check vacuum gauge and monitor warning light for
proper vacuum system operation.
B. Emergency Procedures
1. Primary Vacuum Failure Warning Light Illuminates
a. Pull the Standby Vacuum System knob OUT -ON- and adjust
throttle setting as required to maintain adequate vacuum for the
primary instruments--Suction Gauge Reading in the Green Arc--If
necessary descend to a lower altitude to obtain a larger
differential between manifold and ambient pressure. Vacuum power
must be closely monitored by checking the vacuum gauge frequently.
b. The SVS is not designed for continued IFR flight. Immediate
steps should be taken to return to VFR conditions or to land. If
this
[[Page 36623]]
is not possible, IFR flight should be continued only as long as
necessary to return to VFR conditions or land the airplane.
WARNING: FAILURE OF THE VACUUM SYSTEM STILL CONSTITUTES AN
EMERGENCY SITUATION REGARDLESS OF THE INSTALLATION OF THE SVS. IT
MAY NOT BE POSSIBLE TO MAINTAIN A SAFE ALTITUDE AND MAKE USE OF THE
SVS. IN SUCH A SITUATION THE AIRPLANE MUST BE FLOWN USING NON-VACUUM
POWERED INSTRUMENTS.
c. If descent is impractical:
Periodically and temporarily reduce power as required
to provide adequate vacuum to the aircraft primary instruments.
Reapply power as required, while comparing vacuum
driven gyros against the Turn and Bank Indicator, Turn Coordinator,
VSI and/or other flight instruments.
When an obvious discrepancy is noted between the vacuum
driven instruments and other flight instrumentation. Periodically
and temporarily reduce power as required to provide adequate vacuum
to the aircraft primary instruments.
III. Performance
No change.
Issued in Kansas City, Missouri, on June 25, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-16911 Filed 7-6-99; 8:45 am]
BILLING CODE 4910-13-P