```

[Federal Register Volume 79, Number 209 (Wednesday, October 29, 2014)]
[Rules and Regulations]
[Pages 64306-64311]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-25419]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0431; Directorate Identifier 2013-NM-041-AD; 
Amendment 39-18003; AD 2014-21-09]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2005-14-07 for 
certain The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, 
and 727-200F series airplanes. AD 2005-14-07 required repetitive 
inspections of the carriage attach fittings on the inboard and outboard 
foreflaps of each wing for cracking and other discrepancies, and 
corrective actions if necessary. This new AD requires reducing certain 
repetitive inspection intervals for the inboard and outboard

[[Page 64307]]

carriage attach fittings for the outboard foreflaps, requires 
previously optional terminating actions which install improved outboard 
foreflap carriage attach fittings, and adds new initial and repetitive 
inspections of those fittings and corrective actions if necessary. This 
AD was prompted by a report of broken inboard and outboard carriage 
attach fittings of the outboard foreflaps found during an inspection. 
We are issuing this AD to detect and correct fatigue cracking of the 
attach fittings of the foreflap carriage of the wings, which could 
result in partial or complete loss of the foreflap and consequent loss 
of controllability of the airplane.

DATES: This AD is effective December 3, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 3, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
15, 2005 (70 FR 39647, July 11, 2005).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Aircraft Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0431; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Chandraduth Ramdoss, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712-
4137; phone: 562-627-5239; fax: 562-627-5210; email 
chandraduth.ramdoss@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2005-14-07, Amendment 39-14184 (70 FR 39647, 
July 11, 2005). AD 2005-14-07 applied to certain The Boeing Company 
Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series 
airplanes. The NPRM published in the Federal Register on July 9, 2014 
(79 FR 38801). The NPRM was prompted by a report of broken inboard and 
outboard carriage attach fittings of the outboard foreflaps found 
during an inspection required by AD 2005-14-07. The airplane had 47,125 
flight cycles. Boeing stated that the metallurgical analysis determined 
that the cause of the broken fittings is a suspected static overload 
condition. The NPRM proposed to continue to require repetitive 
inspections of the carriage attach fittings on the inboard and outboard 
foreflaps of each wing for cracking and other discrepancies, and 
corrective actions if necessary. The NPRM also proposed to require 
reducing certain repetitive inspection intervals for the inboard and 
outboard carriage attach fittings for the outboard foreflaps, requiring 
previously optional terminating actions which install improved outboard 
foreflap carriage attach fittings, and adding new initial and 
repetitive inspections of those fittings and corrective actions if 
necessary. We are issuing this AD to detect and correct fatigue 
cracking of the attach fittings of the foreflap carriage of the wings, 
which could result in partial or complete loss of the foreflap and 
consequent loss of controllability of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. Boeing supported the 
NPRM (79 FR 38801, July 9, 2014).

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 38801, July 9, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 38801, July 9, 2014).

Costs of Compliance

    We estimate that this AD affects 98 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                            Retained Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
         Retained action              Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections of the carriage       4 work-hours x $85  None..............  $340 per airplane,  $33,320, per
 attach fittings for all           per hour = $340.                        per inspection      inspection cycle.
 airplanes [retained actions                                               cycle.
 from AD 2005-14-07, Amendment
 39[dash]14184 (70 FR 39647,
 July 11, 2005)].
Installation of guide blocks for  32 work-hours x     $0................  $2,720 per          Up to $266,560.
 certain airplanes [retained       $85 per hour =                          airplane.
 actions from AD 2005-14-07,       $2,720.
 Amendment 39-14184 (70 FR
 39647, July 11, 2005)].
Inspection of foreflap airload    4 work-hours x $85  None..............  $340 per airplane.  Up to $33,320.
 roller travel for certain         per hour = $340.
 airplanes [retained actions
 from AD 2005-14-07, Amendment
 39-14184 (70 FR 39647, July 11,
 2005)].

[[Page 64308]]

 
Modification of the inboard       4 work-hours x $85  $0................  $340 per airplane.  Up to $33,320.
 jackscrews on the outboard flap   per hour = $340.
 for certain airplanes [retained
 actions from AD 2005-14-07,
 Amendment 39-14184 (70 FR
 39647, July 11, 2005)].
Inspection of the entire track    12 work-hours x     None..............  $1,020 per          Up to $99,960.
 and of the track rib faces for    $85 per hour =                          airplane.
 certain airplanes [retained       $1,020.
 actions from AD 2005-14-07,
 Amendment 39-14184 (70 FR
 39647, July 11, 2005)].
----------------------------------------------------------------------------------------------------------------

                                         Estimated Costs for New Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
         Retained action              Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection and functional check   3 work-hours x $85  None..............  $255, per           $24,990, per
 of outboard foreflap              per hour = $255                         inspection cycle.   inspection cycle.
 installation for all airplanes    per inspection
 [new action].                     cycle.
Replacement of carriage attach    2 work-hours x $85  $18,000...........  $18,170 per         Up to $1,780,660.
 fitting on outboard foreflap      per hour = $170.                        airplane.
 for certain airplanes [new
 action].
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement of sequence carriage       2 work-hours x $85 per   Up to $175.............  Up to $345.
 slider or sidewall rubstrips.          hour = $170.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect 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.
    For the reasons discussed above, I certify that this AD:
    (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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), and adding 
the following new AD:

2014-21-09 The Boeing Company: Amendment 39-18003; Docket No. FAA-
2014-0431; Directorate Identifier 2013-NM-041-AD.

(a) Effective Date

    This AD is effective December 3, 2014.

(b) Affected ADs

    This AD replaces AD 2005-14-07, Amendment 39-14184 (70 FR 39647, 
July 11, 2005).

(c) Applicability

    This AD applies to Boeing Model 727, 727C, 727-100, 727-100C, 
727-200, and 727-200F series airplanes, certificated in any 
category, as listed in Boeing Alert Service Bulletin 727-57A0135, 
Revision 3, dated June 27, 2002.

[[Page 64309]]

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of broken carriage attach 
fittings of the inboard and outboard foreflaps found during an 
inspection and an additional report of broken inboard and outboard 
carriage attach fittings of the outboard foreflaps found during an 
inspection. We are issuing this AD to detect and correct fatigue 
cracking of the attach fittings of the foreflap carriage of the 
wings, which could result in partial or complete loss of the 
foreflap and consequent loss of controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Inspections

    This paragraph restates the requirements of paragraph (f) of AD 
2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with 
revised service information and a new compliance time. Except as 
provided by paragraph (l) of this AD: Within 1,000 flight cycles 
after August 15, 2005 (the effective date of AD 2005-14-07) or 
within 6 months after the effective date of this AD, whichever 
occurs first, and thereafter at intervals not to exceed 1,000 flight 
cycles, except as required by paragraph (m) of this AD (for outboard 
foreflaps), inspect as specified in paragraphs (g)(1) and (g)(2) of 
this AD, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 
27, 2002; or Revision 4, dated September 26, 2012. As of the 
effective date of this AD, use only Boeing Alert Service Bulletin 
727-57A0135, Revision 4, dated September 26, 2012. Accomplishing the 
actions of paragraph (m) or (o) of this AD terminates the 
inspections required by this paragraph for outboard foreflaps only.
    (1) A detailed inspection to detect cracks and surface 
deviations on all edges, surfaces, and lug attachment fastener holes 
on the two carriage attach fittings on the inboard and outboard 
foreflaps of each wing.
    (2) A high frequency eddy current (HFEC) inspection to detect 
cracks at the lug attachment fastener holes on the two carriage 
attach fittings on the inboard and outboard foreflaps of each wing.

(h) Retained Replacement

    This paragraph restates the requirements of paragraph (g) of AD 
2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with 
revised service information. If any crack is detected or if any 
surface deviation beyond the limits specified in Boeing Alert 
Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or 
Revision 4, dated September 26, 2012; is detected during any 
inspection required by paragraph (g) or (m) of this AD, before 
further flight, replace the carriage attach fitting with a new, 
improved fitting or a new fitting having the same part number as the 
existing fitting, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 
27, 2002; or Revision 4, dated September 26, 2012. As of the 
effective date of this AD, use only Boeing Alert Service Bulletin 
727-57A0135, Revision 4, dated September 26, 2012.

(i) Retained Measurement and Associated Corrective Action(s)

    (1) This paragraph restates the requirements of paragraph (h) of 
AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with 
revised service information. Within 3,500 flight cycles after August 
15, 2005 (the effective date of AD 2005-14-07), inspect for 
interference between the carriage attach fitting and the carriage 
lug fitting, and do other related investigative actions by 
accomplishing all the actions specified in paragraph 3.C. and Figure 
2 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or paragraph 
3.B.3 and Figure 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 
2012. Do the actions in accordance with Boeing Alert Service 
Bulletin 727-57A0135, Revision 3, dated June 27, 2002; or Revision 
4, dated September 26, 2012. As of the effective date of this AD, 
use only Boeing Alert Service Bulletin 727-57A0135, Revision 4, 
dated September 26, 2012.
    (2) Paragraphs (i)(2)(i) and (i)(2)(ii) of this AD restate the 
requirements of paragraph (i) of AD 2005-14-07, Amendment 39-14184 
(70 FR 39647, July 11, 2005), with revised service information.
    (i) If any discrepancy is found during any action required by 
paragraph (i)(1) of this AD, before further flight, accomplish 
applicable corrective action(s) (e.g., adding a shim or reworking 
the carriage attachment lug assembly), in accordance with paragraph 
3.C. and Figure 2 or 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002; 
or paragraph 3.B.3. and Figure 3 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated 
September 26, 2012; except as required by paragraph (i)(2)(ii) of 
this AD. As of the effective date of this AD, use only Boeing Alert 
Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012.
    (ii) Where Boeing Alert Service Bulletin 727-57A0135, Revision 
3, dated June 27, 2002; or Revision 4, dated September 26, 2012; 
specify to contact the manufacturer if rework of the improved 
fitting is required: Before further flight, rework in accordance 
with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), or Los Angeles ACO, FAA; or in 
accordance with data meeting the type certification basis of the 
airplane approved by an Authorized Representative (AR) for the 
Boeing Delegation Option Authorization (DOA) Organization who has 
been authorized by the FAA to make such findings; or using a method 
approved in accordance with the procedures specified in paragraph 
(s) of this AD. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically reference this AD. As of the effective date of this AD, 
any new repair approval must be done using a method approved in 
accordance with the procedures specified in paragraph (s) of this 
AD.

(j) Retained Concurrent Requirements

    (1) This paragraph restates the requirements of paragraph (j) of 
AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with 
new paragraph reference. For Model 727 airplanes listed in Boeing 
727 Service Bulletin 57-59, Revision 1, dated September 27, 1965: 
Before or at the same time with the requirements of paragraph (i) or 
(o) of this AD, install guide blocks and bushings in the midflap 
ribs in accordance with the Accomplishment Instructions of Boeing 
727 Service Bulletin 57-59, Revision 1, dated September 27, 1965.
    (2) This paragraph restates the requirements of paragraph (k) of 
AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with 
new paragraph reference. For Model 727 airplanes listed in Boeing 
Service Bulletin 727-27-133, Revision 1, dated May 9, 1972: Before 
or at the same time with the requirements of paragraph (i) or (o) of 
this AD, do the actions specified in paragraphs (j)(2)(i) and 
(j)(2)(ii) of this AD, as applicable.
    (i) For Groups I and II airplanes identified in Boeing Service 
Bulletin 727-27-133, Revision 1, dated May 9, 1972: Do a one-time 
inspection of the airload support roller for travel on the foreflap 
track, in accordance with Part I of the Accomplishment Instructions 
of Boeing Service Bulletin 727-27-133, Revision 1, dated May 9, 
1972.
    (A) If the airload support roller travels within the limits 
specified in Boeing Service Bulletin 727-27-133, Revision 1, dated 
May 9, 1972, modify the control drum of the inboard flap and inboard 
jackscrews of the outboard flap, in accordance with Part II of the 
Accomplishment Instructions of Boeing Service Bulletin 727-27-133, 
Revision 1, dated May 9, 1972.
    (B) If the airload support roller travels beyond the limits 
specified in Boeing Service Bulletin 727-27-133, Revision 1, dated 
May 9, 1972, repair in accordance with a method approved by the 
Manager, Seattle ACO, or Los Angeles ACO, FAA; or in accordance with 
data meeting the type certification basis of the airplane approved 
by an AR for the Boeing DOA Organization who has been authorized by 
the FAA to make such findings; or using a method approved in 
accordance with the procedures specified in paragraph (s) of this 
AD. For a repair method to be approved, the repair must meet the 
certification basis of the airplane, and the approval must 
specifically reference this AD. As of the effective date of this AD, 
any new repair approval must be done using a method approved in 
accordance with the procedures specified in paragraph (s) of this 
AD.
    (ii) For Group III airplanes identified in Boeing Service 
Bulletin 727-27-133, Revision 1, dated May 9, 1972: Modify the 
inboard jackscrews of the outboard flap (i.e., replacing the down 
stop at the inboard jackscrews of the outboard flap) in accordance 
with Part II of the

[[Page 64310]]

Accomplishment Instructions of Boeing Service Bulletin 727-27-133, 
Revision 1, dated May 9, 1972.
    (3) This paragraph restates the requirements of paragraph (l) of 
AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with 
new paragraph reference. For Model 727 airplanes listed in Boeing 
727 Service Bulletin 57-72, dated September 21, 1966: Before or at 
the same time with the requirements of paragraph (i) or (o) of this 
AD, do the actions specified in paragraphs (j)(3)(i) through 
(j)(3)(iv) of this AD.
    (i) Chamfer the upper and lower flanges at the aft end of the 
foreflap tracks in accordance with the Accomplishment Instructions 
of Boeing 727 Service Bulletin 57-72, dated September 21, 1966.
    (ii) Do a standard magnetic particle inspection of the entire 
foreflap tracks for cracks in accordance with the Accomplishment 
Instructions of Boeing 727 Service Bulletin 57-72, dated September 
21, 1966. If any crack is detected, before further flight, repair in 
accordance with a method approved by the Manager, Seattle ACO, or 
Los Angeles ACO, FAA; or in accordance with data meeting the type 
certification basis of the airplane approved by an AR for the Boeing 
DOA Organization who has been authorized by the FAA to make such 
findings; or using a method approved in accordance with the 
procedures specified in paragraph (s) of this AD. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically reference this 
AD. As of the effective date of this AD, any new repair approval 
must be done using a method approved in accordance with the 
procedures specified in paragraph (s) of this AD.
    (iii) Do a general visual inspection of the track rib faces at 
the front and rear spars to verify if the opening in the spars is 
flush with or clear of the plane of the rib faces, in accordance 
with the Accomplishment Instructions of Boeing 727 Service Bulletin 
57-72, dated September 21, 1966. If the opening is not flush or 
clear with the plane, before further flight, rework the spar opening 
in accordance with the Accomplishment Instructions of Boeing 727 
Service Bulletin 57-72, dated September 21, 1966.
    (iv) Do a general visual inspection of the head or shank of 
bolts by securing the foreflap links to the foreflap tracks to 
verify if they protrude beyond the edge of the track flange in 
accordance with the Accomplishment Instructions of Boeing 727 
Service Bulletin 57-72, dated September 21, 1966. If the head or 
shank of the bolts protrude beyond the edge of the track flange, 
before further flight, rework in accordance with the Accomplishment 
Instructions of Boeing 727 Service Bulletin 57-72, dated September 
21, 1966.
    (v) For the purposes of this AD, a general visual inspection is 
defined as: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
enhance visual access to all exposed surfaces in the inspection 
area. This level of inspection is made under normally available 
lighting conditions such as daylight, hangar lighting, flashlight, 
or droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''
    (4) This paragraph restates the requirements of paragraph (m) of 
AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with 
a new paragraph identifier. For airplanes other than those 
identified in the service information specified in paragraphs (j)(1) 
through (j)(3) of this AD: Before or at the same time with the 
requirements of paragraph (i) or (o) of this AD, do an inspection to 
verify if any of the parts listed in the ``Spares Affected'' 
paragraph of each service information referenced in paragraphs 
(j)(1) through (j)(3) of this AD are installed on the airplane. If 
any part identified in that paragraph is found installed, before 
further flight, do the applicable corrective and investigative 
action(s) specified in paragraphs (j)(1) through (j)(3) of this AD.

(k) Retained Optional Terminating Actions

    This paragraph restates the requirements of paragraph (n) of AD 
2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), with no 
changes. Replacement of the two carriage attach fittings on the 
inboard and outboard foreflaps of each wing with new, improved 
fittings, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June 
27, 2002; and accomplishment of the actions specified in paragraphs 
(j)(1) through (j)(4) of this AD, as applicable, before or 
concurrently with the replacement; constitutes terminating action 
for paragraphs (g) through (j) of this AD and paragraph (l) of this 
AD for those replaced fittings on the outboard and inboard 
foreflaps.

(l) Retained Optional Deferral of Inspection

    This paragraph restates the optional deferral of paragraph (o) 
of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), 
with no changes. Replacement of the two carriage attach fittings on 
the inboard and outboard foreflaps of each wing with new fittings 
having the same part number as the existing fittings, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 727-57A0135, Revision 3, dated June 27, 2002; and 
accomplishment of the actions specified in paragraphs (j)(1) through 
(j)(4) of this AD, as applicable, before or concurrently with the 
replacement; defers the next inspection required by paragraph (g) of 
this AD for 10,000 flight cycles after the replacement. Thereafter, 
repeat the inspections required by paragraph (g) of this AD at 
intervals not to exceed 1,000 flight cycles, except as required by 
paragraph (m) of this AD.

(m) New Detailed and HFEC Inspections of Outboard Foreflaps, With 
Reduced Repetitive Intervals

    Within 1,000 flight cycles after the most recent accomplishment 
of the inspections required by paragraph (g) of this AD, do a 
detailed inspection to detect cracks and surface deviations on all 
edges, surfaces, and lug attachment fastener holes, and a HFEC 
inspection to detect cracks at the lug attachment fastener holes, on 
the two carriage attach fittings on the outboard foreflaps of each 
wing, in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 727-57A0135, Revision 4, dated September 26, 
2012, and do all applicable corrective actions required by paragraph 
(h) of this AD. Repeat the inspections thereafter at intervals not 
to exceed 200 flight cycles until the requirements of paragraph (o) 
of this AD is accomplished. Accomplishing the requirements of this 
paragraph terminates the requirements of paragraph (g) of this AD 
for the outboard foreflaps only.

(n) New Inspection and Check of Outboard Foreflap Installation and 
Corrective Action

    Within 200 flight cycles or 6 months after the effective date of 
this AD, whichever occurs first, do a general visual inspection and 
function check for damage and incorrect operation of the outboard 
foreflap installations, and all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. 
Do the applicable corrective actions before further flight. 
Thereafter, repeat the inspection and check at intervals not to 
exceed 500 flight cycles.

(o) New Replacement of Previously Un-Replaced (or ``Original 
Configuration'') Carriage Attach Fittings on the Outboard Foreflap

    For airplanes on which any production carriage attach fitting is 
still installed on the outboard foreflap: Within 3,000 flight cycles 
or 3 years after the effective date of this AD, whichever occurs 
first, replace all production carriage attach fittings with new, 
improved carriage attach fittings, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 727-
57A0135, Revision 4, dated September 26, 2012, and do all applicable 
concurrent actions required by paragraph (k) of this AD. 
Accomplishing the requirements of this paragraph terminates the 
requirements of paragraphs (g) and (m) of this AD for outboard 
foreflaps only.

(p) New Inspection, Corrective Action and Replacement of Fittings 
Replaced in Accordance With Paragraph (l) of This AD

    For airplanes on which a new carriage attach fitting with the 
original part number on the outboard foreflap was installed in 
accordance with paragraph (l) of this AD: Do the actions specified 
in paragraphs (p)(1) and (p)(2) of this AD.
    (1) Within 1,000 flight cycles after the effective date of this 
AD, do a detailed inspection for cracks and surface deviation on all 
edges surfaces, and lug attachment fastener holes, and a HFEC 
inspection for cracks at the lug attachment fastener holes, on the 
carriage attach fittings for the outboard foreflaps, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 
4, dated September 26, 2012. Repeat the inspection at intervals not 
to exceed 200

[[Page 64311]]

flight cycles. Do all applicable corrective actions before further 
flight.
    (2) Within 3,000 flight cycles or 3 years after the effective 
date of this AD, replace the fitting with a new, improved fitting in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 727-57A0135, Revision 4, dated September 26, 2012. 
Accomplishing the requirements of this paragraph terminates the 
requirements of paragraphs (g), (m), and (p)(1) of this AD for that 
outboard foreflap only.

(q) New Inspection and Corrective Actions on Fittings Replaced 
According to Paragraph (k), (o), or (p) of This AD on Outboard 
Foreflaps

    For airplanes on which a new, improved carriage attach fitting 
on the outboard foreflap was replaced in accordance with the 
requirements of paragraph (k), (o), or (p) of this AD: Within 20,000 
flight cycles after installing that fitting, do a detailed 
inspection for cracks and surface deviation on all edges surfaces, 
and lug attachment fastener holes, and a HFEC inspection for cracks 
at the lug attachment fastener holes, on the carriage attach 
fittings for the outboard foreflaps, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 727-57A0135, Revision 
4, dated September 26, 2012. Do all applicable corrective actions 
before further flight. Repeat the inspection thereafter at intervals 
not to exceed 1,400 flight cycles. Accomplishing the requirements of 
this paragraph terminates the requirements of paragraph (g) of this 
AD for outboard foreflaps only.

(r) Retained Credit for Previously Accomplished Service Bulletins

    (1) This paragraph restates the credit provided by paragraph (p) 
of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), 
with no changes. Installations accomplished before August 15, 2005 
(the effective date of AD 2005-14-07), in accordance with Boeing 727 
Service Bulletin 57-59, dated September 2, 1965, are acceptable for 
compliance with the requirements of paragraph (j)(1) of this AD.
    (2) This paragraph restates the credit provided by paragraph (q) 
of AD 2005-14-07, Amendment 39-14184 (70 FR 39647, July 11, 2005), 
with no changes. Inspections and modifications accomplished before 
August 15, 2005 (the effective date of AD 2005-14-07), in accordance 
with Boeing Service Bulletin 727-27-133, dated October 7, 1971, are 
acceptable for compliance with the requirements of paragraph (j)(2) 
of this AD.

(s) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (t)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Los Angeles ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.
    (4) AMOCs approved for AD 2005-14-07, Amendment 39-14184 (70 FR 
39647, July 11, 2005), are approved as AMOCs for the corresponding 
provisions of this AD.

(t) Related Information

    (1) For more information about this AD, contact Chandraduth 
Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; 
email chandraduth.ramdoss@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (u)(5) and (u)(6) of this AD.

(u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
December 3, 2014.
    (i) Boeing Alert Service Bulletin 727-57A0135, Revision 4, dated 
September 26, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
August 15, 2005 (70 FR 39647, July 11, 2005).
    (i) Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated 
June 27, 2002.
    (ii) Boeing Service Bulletin 727-27-133, Revision 1, dated May 
9, 1972. Pages 1, 12, 14 through 18, and 27 of this document are 
identified as Revision 1, dated May 9, 1972. Pages 2 through 11, 13, 
19 through 26, and 28 are original, dated October 7, 1971.
    (iii) Boeing 727 Service Bulletin 57-59, Revision 1, dated 
September 27, 1965. Pages 1, 4, and 6 of this document are 
identified as Revision 1, dated September 27, 1965. Pages 2, 3, and 
5 are original, dated September 2, 1965.
    (iv) Boeing 727 Service Bulletin 57-72, dated September 21, 
1966.
    (5) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (6) You may view this referenced service information at the FAA, 
Transport Aircraft Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-25419 Filed 10-28-14; 8:45 am]
BILLING CODE 4910-13-P
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