SERVICE No.
571A
PIPER BULLETIN
- Piper Aircraft Corporation Lock Haven, Pennsylvania, U.S.A.
"DOA SO-1 Approved" October 20, 1977 S
(Supersedes Service Bulletin No. 571 dated May 26, 1977)
This Service Bulletin consists of four (4) parts (A through D, below); each part must
be reviewed carefully to determine the effectivity status of your aircraft.
PART A
Subject: Fuel Valve Leak Check
Reason for Revision: (1) Additional valve installation kit (see Note*,
below, Instructions No. 5 and Material Required);
and (2) certain valve installation kits may be
affected by leak check - see Note*, below.
Models Affected: Serial Numbers Affected:
PA-28-235 Cherokee.......................28-10001 to 28-7410093 incl.,
PA-32-260 Cherokee Six...................32-03, 32-04, 32-1 to 32-7400049 incl.,
PA-32-300 Cherokee Six ...................32-15, 32-21, 32-40000 to 32-7440160 incl.,
PA-32S-300 Cherokee Six ..................32S-15, 32S-40000 to 32S-7240137 incl.
Special Note: The aircraft listed above originally had one of the following fuel selector
valves installed:
Piper Part Number Airborne Model No.
492 083 ........................................ 1-H10
492 099 ........................................ 1-H16-1
492 104 ........................................ 1-H26-2
492 125 ........................................ 1-H26-3
492 171 ........................................ 1-H26-4
If any of the above fuel selector valves have been replaced by one of the following valves
or valve installation kits listed below, then PART A of this Service Bulletin does not
apply (except as stated in Note*, below):
NOTE*
Earlier configuration valve installation kits 757 148V and 757 158V contained a fuel selector
valve other than. (valve model no.) 1-H65-2 and are affected by Part A (visually check valve
model no. to determine effectivity).
(continued)
I Service Bulletin No. 571A Page 2 of 7
Piper Valve/Kit Part Number Airborne Valve Model No.
492 259..................................1-H65-2
492 262..................................1-H65-3
*757 148V ................................ 1-H65-2
I *757 158V ................................ 1-H65-2
760 895V................................ 1-H65-2
Compliance Time: Within the next five (5) hours and repeated prior to the first flight
of each day until compliance with PART A through PART D of this Service Bulletin is
accomplished. If full compliance with the original issue of this Service Bulletin has
been achieved and the revised information contained herein does not apply to your aircraft,
then this revised "A" issue does not apply. After compliance, valve should be checked
for leaks after each fifty (50) hours of operation.
Purpose: Inter-port leakage within the fuel selector valve could cause fuel transfer
from one tank to another resulting in possible fuel mismanagement. Additional fuel
system malfunctions, when combined with a leaking fuel selector valve, may result in air
ingestion, rough engine operation or power interruption.
Instructions:
1. Position aircraft on relatively level ground with a minimum of one (1) gallon in each
tank. Drain fuel tank sumps and fuel selector sump using normal preflight procedures.
SPECIAL NOTE:
Observe all safety precautions required when handling gasoline.
2. With fuel selector in the "OFF" position, drain fuel selector by operating drain lever
through the access panel located on the right side of the cabin on the forward edge of
the wing spar housing. Valve should be held "open" for one minute. Collect contents
and discard. NOTE: Because of residual fuel in the fuel selector sump bowl, several
attemps may be required to drain all fuel from the sump bowl. A leaking fuel valve
is indicated by continued draining when the fuel selector is in the "OFF" position.
The volume of this drainage depends on the size of the leak.
3. Close drain valve and wait three minutes. Drain fuel selector for one minute, collecting
contents in a graduated container. Close drain valve. Contents collected must be less
than 1/2fluid ounce.
4. If fuel collected exceeds one half fluid ounce, repeat Item 3, above.
5. If repeated collected fuel exceeds one half fluid ounce, an excessive internal leaking
fuel selector is indicated. Remove and clean the fuel selector valve or replace fuel
valve with Piper Kit No. 757 148V, 757 158V or 760 895V.
Make proper log book entry as to compliance with PART A of this Service Bulletin.
NOTE: The leak check described above can be accomplished by the pilot/owner.
Material Required: See Instructions, Step 5, above; Kits 757 148V, 757 158V and 760 895V
are available at a special reduced price of $154.09E, $148.17E and $179.14E respectively.
Refer to Piper Parts Catalog for correct valve replacement kit for aircraft serial numbe
affected.
(continued)
Service Bulletin No. 571A Page 3 of 7 I
PART B
Subject: Fuel Cap Replacement
Models Affected: Serial Numbers Affected:
PA-28-235 Cherokee ....................... 28-10001 to 28-11236 incl.,
PA-32-260 Cherokee Six...................32-03, 32-04, 32-1 to 32-1123 incl.,
PA-32-300 Cherokee Six...................32-15, 32-21, 32-40000 to 32-40629 incl.,
PA-32S-300 Cherokee Six .................. 32S-15, 32S-40000 to 32S-40629 incl.
Compliance Time: Within the next one hundred hours time in service after effective date
of this Service Bulletin. SPECIAL NOTE: If caps are inspected prior to the above
compliance time and replacement caps are not available, you may continue to fly the air-
craft to the 100 hour maximum time by complying with the daily fuel valve leak check as
required in PART A of this Service Bulletin.
Purpose: To provide material and instructions for replacement of fuel caps.
Instructions: Remove all fuel caps from aircraft and inspect to determine if replacement is
necessary. This determination is easily accomplished, as the proper fuel cap contains a
red rubber check valve visible in the center of its under surface. Other configurations
are unacceptable and must be replaced. Make a proper log book entry as to compliance with
PART B of this Service Bulletin.
NOTE:
The fuel cap replacement described above can be accomplished by the pilot/owner.
Material Required: Four (4) each maximum per aircraft, Piper Part Number 66817-OOV,
Fuel Cap @ special reduced unit price of $5.33J.
PART C
Subject: Fuel Tank Vent Check
Models Affected: Serial Numbers Affected:
PA-28-235 Cherokee............. .......... 28-10001 to 28-7710040 incl.,
PA-32-260 Cherokee Six......... .......... 32-13, 32-14, 32-1 to 32-7700016 incl.,
PA-32-300 Cherokee Six......... .......... 32-15, 32-21, 32-40000 to 32-7740037 incl.,
32-7740039 to 32-7740053 incl., 32-7740055
to 32-7740062 incl., 32-7740064 to 32-7740069 incl.,
PA-32S-300 Cherokee Six........ .......... 32S-15, 32S-40000 to 32S-7240137 incl.
Compliance Time: Within the next fifty (50) hours or an inspection time period, whichever
occurs first.
(continued)
I Service Bulletin No. 571A PART C (continued) Page 4 of 7
Purpose: It has been determined that some fuel tank vents which have been modified per
Service Bulletin No. 342 may not conform to Piper's specifications; in addition vents
may have been bent or misaligned in service. Therefore, PART C of this Service Bulletin
is being issued to provide tolerances and methods of checking the fuel tank vents.
Instructions: SPECIAL NOTE: Before proceeding with the Instructions below, Piper Service
Bulletin No. 342, pages 2 and 3 - if not already complied with - must be accomplished.
1. Fabricate templates using full scale illustrations attached to this Service Bulletin,
from plastic, aluminum or other suitable rigid material.
(heck tip tank fuel vent scarf angle and position relative to the lower surface of the
wing using template "A". The scarf angle must be 60 to 65 and normal (90 ) to the
lower surface of the wing, plus or minus 2 .
J. Check main tank fuel vent scarf angle and position relative to the lower surface of
the wing using template "B". The scarf angle must be 400 plus or minus 2 and normal
(90) to the lower surface of the wing, plus or minus 2 .
4. The plane of the scarf angle and the .062 vent hole of the tip fuel tank vent tube
may be rotated (left or right) from the direction of flight to a maximum of 30 .
5. The plane of the scarf angle and the .090 vent hole of the main fuel tank vent tube
may be rotated (left or right) from the direction of flight to a maximum of 5 .
6. Inspect tip tank fuel vent to determine if a .062" hole is drilled on the aft side
of the vent. If no hole exists use template "A" for location and drill a .062"
hole through the aft side only.
7. Inspect main tank fuel vent to determine if a .090" hole is drilled on the aft side
of the vent. If no hole exists use template "B" for location and drill a .090"
hole through the aft side only.
8. Make a proper log book entry as to compliance with PART C of this Service Bulletin.
NOTE:
Some tip tanks were not equipped with protruding vents; therefore,
PART C, Items 2, 4 and 6 of this Service Bulletin do not apply
to those tanks.
PART D
Subject: Fuel Line Inspection
Models Affected: Serial Numbers Affected:
PA-28-235 Cherokee ....................... 28-10001 to 28-7710040 incl.,
PA-32-260 Cherokee Six ................... 32-03, 32-04, 32-1 to 32-7700016 incl.,
PA-32-300 Cherokee Six...................32-15, 32-21, 32-40000 to 32-7740037 incl.,
32-7740039 to 32-7740053 incl., 32-7740055 to
7740062 incl., 32-7740064 to 32-7740069 incl.,
PA-32S-300 Cherokee Six .................. 32S-15, 32S-40000 to 32S-7240137 incl.
(continued)
Service Bulletin No. 571A PART D (continued) Page 5 of 7
I
Compliance Time: Within the next fifty (50) hours or an inspection time period,which-
ever occurs first.
Purpose: The possibility of improper installation of the flexible hose assembly (Piper
Part No. 63901-15 or -48) exists. Therefore, a fuel line inspection is required.
Instructions: (See sketch below)
1. Disconnect the main landing gear strut fairings from the wing, lower or remove
from aircraft.
2. Remove the main landing gear access cover and visually inspect flexible hose assembly.
This hose assembly must not show signs of twist. If the hose assembly is twisted,
loosen end fitting and allow line to return to its natural state. Slight hand pressure
may be needed. If the flex hose assembly fails to return to its natural state or if
excessive hand pressure is required, the hose assembly must be replaced.
SPECIAL NOTE
Latest Piper Service Manual recommends replacement of the flexible
hose assembly at recommended engine overhaul periods.
Material Required: (Maximum) two each per aircraft Flexible Hose Assembly, Piper
Part Numbers 63901-15V and 63901-48V @ suggested unit list price $9.32C and $9.32C,
respectively.
Cover Assembly
63901-15V or -48V
Flexible Hose Assembly
Fairing Assembly
Main Gear Strut
Service Bulletin No. 571A (continued) Page 6 of 7
Availability of Parts: Your Piper Field Service Facility.
Effectivity Date: This Service Bulletin is effective upon receipt.
Summary: Please carefully review the four sections of this Service Release for
applicability to your airplane, and your subsequent course of action. Please contact
your Piper Field Service Facility to make arrangements for appropriate compliance,
in accordance with Compliance Time requirements specified in each individual section.
Page 7 of 7
Lower Surface
Of Tip Tank
50/. 75
60 to 65
FWD
Template A
TIP TANK VENT
Lower Surface of
90 2 Main Tank
Hole
1. 16 . 06
.90 ± . 03
40 ° ± 2 °
FWD
<-— Template B
REF:S.B. #571A
MAIN TANK VENT Part "C"
