FAA SPECIAL AIRWORTHINESS
Aviation Safety INFORMATION BULLETIN
SAIB: CE-17-12
SUBJ: Horizontal Stabilizer – Elevator Attach Points Date: May 11, 2017
This is information only. Recommendations aren’t mandatory.
Introduction
This Special Airworthiness Information Bulletin alerts owners, operators, maintenance technicians,
and inspectors of an airworthiness concern, specifically for the potential of loose bolts at the elevator
attach points on Textron Aviation Inc. (Cessna Aircraft Company) 150 and 152 (all models listed
in Table 1 of this SAIB) airplanes.
At this time, the Federal Aviation Administration (FAA) has determined that this airworthiness
concern is not an unsafe condition that would warrant airworthiness directive action under Title 14 of
the Code of Federal Regulations (14 CFR) part 39.
Background
The FAA recently received a report through the Safety Difficulty Reporting (SDR) system of the
elevator hinge bolt backing out on Cessna Model 150 airplanes. This allowed the elevator to separate
from the horizontal stabilizer in-flight, which resulted in reduced controllability in the pitch axis. The
main issues identified include excessively worn attach hardware and the use of incorrect attach
hardware. Corrosion may have been a contributing factor in some instances. We found seven similar
reports after further review of SDR’s going back to 1979. The design used to attach the elevator to
the airplane is common among the models of airplanes listed in Table 1 of this SAIB.
Model S/N
617, 628, 644, 649, 17001 - 17999, 59001 - 59018,
150
15059019 - 15079405
A150 A15000001 - A1500734
A-150 A-1501001 - A-1501039
A-A150 A-A1500001 - A-A1500009
F150 F150-0001 - F150-0529, F15000530 - F15001428
FA150 FA1500001 - FA1500120
FRA150 FRA1500121 - FRA1500336
152 15279406 - 15286033
A152 A15200735 - A15201049
FA152 FA15200337 - FA1520425
F152 F15201449 - F15201980
Table 1. Affected Airplane Models
1
Recommendations
The FAA recommends performing the inspections detailed in the Cessna supplemental inspection
document (SID) 55-10-01. If worn or incorrect hardware is found, it should be replaced according to
the instructions in the SID.
For Further Information Contact
Adam Hein, Aerospace Engineer, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946-4116;
fax: (316) 946-4107; e-mail:
[email protected].
For Related Service Information Contact
Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A.; phone: (316) 517-
5800; fax: (316) 517-7271.
2
CESSNA AIRCRAFT COMPANY
MODEL 150 SERIES (1969 - 1976)
SERVICE MANUAL
SUPPLEMENTAL INSPECTION NUMBER: 55-10-01
1. TITLE:
Horizontal Stabilizer, Elevators and Attachments Inspection
2. EFFECTIVITY
15069309 thru 15078505,
F15000390 thru F15001338,
A15000001 thru A1500684,
FA15000001 thru FA1500120,
FRA1500121 thru FRA1500311
INSPECTION COMPLIANCE
ALL USAGE: INITIAL 10,000 Hours or 20 Years (NOTE)
REPEAT 2,000 Hours or 4 Years (NOTE)
NOTE: Refer to Note 1, Section 2A-14-00.
3. PURPOSE
To inspect horizontal stabilizer, elevator and attachments for signs of damage, fatigue or deterioration.
4. INSPECTION INSTRUCTIONS
A. Open all stabilizer and elevator access panels, including the stinger and vertical stabilizer to horizontal
tail fairings. Refer to the applicable Model 150 Service Manual.
B. Visually inspect stabilizer and elevator for condition, cracks and security; hinge bolts, hinge bearings
for condition and security; bearings for freedom of rotation; attach fittings for evidence of damage,
wear, failed fasteners and security. Refer to Figure 1.
(1) Clean area before inspecting if grime or debris is present.
(2) If cracks or frozen bearings are found, conduct a surface eddy current inspection. Refer
to Section 2A-13-01 Nondestructive Inspection Methods and Requirements, Eddy current
Inspection - (Surface Inspection), for additional instructions. The inspection is for the aluminum
structure outside of the bearing, so set the instrument for aluminum.
C. Visually inspect the elevator torque tube for corrosion and rivet security. Pay particular attention to
the flange riveted onto the torque tube near the airplane centerline for corrosion. Refer to Figure 1,
Detail F.
(1) Clean area before inspecting if grime or debris is present.
D. Using a borescope inspect forward and aft stabilizer and elevator spars, ribs and attach fittings for
cracks, corrosion, loose fasteners, elongated fastener attach holes, signs of fatigue and deterioration.
(1) Clean area before inspecting if grime or debris is present.
(2) Pay particular attention to the skins at the location where stringers pass through ribs and at the
leading edge skin close to the fuselage. Apply finger pressure at the stringer intersection or the
rib to spar juncture to check for free play indicating a broken rib.
(3) With the inspection plate on top of the horizontal stabilizer removed, pay particular attention to
the forward side of the aft spar where the 0432001–15 reinforcement and 0432004 bracket are
installed. Refer to Figure 1, Detail B.
(4) Visually inspect the forward stabilizer attachment bulkhead for loose rivets and cracks.
(5) Visually inspect the forward side of the front spar.
E. Gain access to the 0432004 bracket. Remove both the 0432004 bracket and 0432001–15
reinforcement from the horizontal aft spar and visually inspect for cracks.
(1) Clean area before inspecting if grime or debris is present.
D971-3-13 Temporary Revision Number 6 - Dec 1/2011 2A-14-10 Page 1
© Cessna Aircraft Company Jun 15/1975
CESSNA AIRCRAFT COMPANY
MODEL 150 SERIES (1969 - 1976)
SERVICE MANUAL
F. Visually inspect the trailing edge portion of the elevator for indications of cracks, corrosion and
deterioration. Visually inspect the attachment of the trim tab horn to the trim tab. Refer to Figure 1,
Detail E.
G. Install all previously removed access panels according to the applicable Model 150 Service Manual.
5. ACCESS AND DETECTABLE CRACK SIZE
ACCESS/LOCATION DETECTABLE CRACK SIZE
Horizontal Tail Not Allowed
6. INSPECTION METHOD
Visual and Eddy Current
7. REPAIR/MODIFICATION
Replace damaged bolts and nuts. Replace damaged fittings and small parts. Replace damaged or
loose rivets. Hinge bearings are prepacked with grease, which will eventually oxidize and harden
after years of service. Several applications of penetrating oil will help free up a stiff bearing. It is the
owner/operator option to replace stiff bearings. Repairs may be made in accordance with Section 18
(Structural Repair) of the applicable Model 150 Service Manual. Any repair not available in Section
18 should be coordinated with Cessna Customer Service prior to beginning the repair.
8. COMMENTS
Coordinate this inspection with SID 55-30-01, Vertical Stabilizer, Rudder and Attachments Inspection.
D971-3-13 Temporary Revision Number 6 - Dec 1/2011 2A-14-10 Page 2
© Cessna Aircraft Company Jun 15/1975
CESSNA AIRCRAFT COMPANY
MODEL 150 SERIES (1969 - 1976)
SERVICE MANUAL
HORIZONTAL STABILIZER, ELEVATORS AND ATTACHMENTS INSPECTION
Figure 1 (Sheet 1)
D971-3-13 Temporary Revision Number 6 - Dec 1/2011 2A-14-10 Page 3
© Cessna Aircraft Company Jun 15/1975
CESSNA AIRCRAFT COMPANY
MODEL 150 SERIES (1969 - 1976)
SERVICE MANUAL
HORIZONTAL STABILIZER, ELEVATORS AND ATTACHMENTS INSPECTION
Figure 1 (Sheet 2)
D971-3-13 Temporary Revision Number 6 - Dec 1/2011 2A-14-10 Page 4
© Cessna Aircraft Company Jun 15/1975
Please find attached a Foreign State of Design Advisory document, endorsed by EASA.
This advisory document is also online at https://ad.easa.europa.eu/ad/CE-17-12 .
Should you have any questions, please contact the Agency by e-mail at
[email protected] or by fax,
No.: +49 221 89990 9515.
Safety Information Section Email:
[email protected]
EASA Website
(Attachment is in Acrobat PDF format)
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