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Boeing concurred with the NPRM (79 

FR 30498, May 28, 2014). 

Conclusion 

We reviewed the available data, 

including 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 

30498, May 28, 2014); and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 30498, 

May 28, 2014). 

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. 

Regulatory Findings 

We 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 the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0285; 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, any comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2012–26–15, Amendment 39–17310 (78 

FR 1735, January 9, 2013), and adding 

the following new AD: 

2012–26–15 R1 Honeywell International 

Inc.: Amendment 39–17990; Docket No. 

FAA–2014–0285; Directorate Identifier 

2014–NM–035–AD. 

(a) Effective Date 

This AD becomes effective December 3, 

2014. 

(b) Affected ADs 

This action rescinds AD 2012–26–15, 

Amendment 39–17310 (78 FR 1735, January 

9, 2013). 

(c) Applicability 

This action applies to air data pressure 

transducers, as installed in air data 

computers (ADC), air data modules (ADM), 

air data attitude heading reference systems 

(ADAHRS), and digital air data computers 

(DADC) having the part numbers and serial 

numbers identified in Honeywell Alert 

Service Bulletin ADM/ADC/ADAHRS–34– 

A01, dated November 6, 2012. This appliance 

is installed on, but not limited to, the aircraft 

specified in paragraphs (c)(1) through (c)(16) 

of this AD. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–111, –211, –212, 

–214, –231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(5) Airbus Model A330–223F, –243F, –201, 

–202, –203, –223, –243, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(6) Airbus Model A340–211, –212, –213, 

–311, –312, –313, –541, and –642 airplanes. 

(7) AGUSTA S.p.A. Model AW139 

helicopters. 

(8) Bell Helicopter Textron Canada Limited 

Model 429 helicopters. 

(9) The Boeing Company Model 767–200, 

–300, –300F, and –400ER series airplanes; 

and Model 777–200, –200LR, –300, –300ER, 

and 777F series airplanes. 

(10) Cessna Aircraft Company Model 

560XL (560 Excel and 560 XLS) airplanes. 

(11) Dassault Aviation Model MYSTERE– 

FALCON 900 airplanes and Model FALCON 

2000 airplanes. 

(12) Empresa Brasileira de Aeronautica 

S.A. (EMBRAER) Model EMB–135BJ 

airplanes. 

(13) Gulfstream Aerospace Corporation 

Model GIV–X and GV–SP airplanes. 

(14) Learjet Inc. Model 45 airplanes. 

(15) PILATUS AIRCRAFT LTD. Model PC– 

12/47E airplanes. 

(16) Viking Air Limited (Type Certificate 

previously held by Bombardier Inc.; de 

Havilland, Inc.) Model (Twin Otter) DHC–6– 

400 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34, Navigation. 

Issued in Renton, Washington, on 

September 23, 2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–24558 Filed 10–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

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 


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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

Retained action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspections of the carriage attach fittings for 

all airplanes [retained actions from AD 

2005–14–07, Amendment 39-14184 (70 

FR 39647, July 11, 2005)].

4 work-hours × $85 

per hour = $340.

None .......................... $340 per airplane, per 

inspection cycle.

$33,320, per inspection cycle. 

Installation of guide blocks for certain airplanes [retained actions from AD 2005– 

14–07, Amendment 39–14184 (70 FR 

39647, July 11, 2005)].

32 work-hours × $85 

per hour = $2,720.

$0 ............................... $2,720 per airplane .... Up to $266,560. 

Inspection of foreflap airload roller travel for 

certain airplanes [retained actions from AD 

2005–14–07, Amendment 39–14184 (70 

FR 39647, July 11, 2005)].

4 work-hours × $85 

per hour = $340.

None .......................... $340 per airplane ....... Up to $33,320. 


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RETAINED ESTIMATED COSTS—Continued 

Retained action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Modification of the inboard jackscrews on the 

outboard flap for certain airplanes [retained actions from AD 2005–14–07, 

Amendment 39–14184 (70 FR 39647, July 

11, 2005)].

4 work-hours × $85 

per hour = $340.

$0 ............................... $340 per airplane ....... Up to $33,320. 

Inspection of the entire track and of the track 

rib faces for certain airplanes [retained actions from AD 2005–14–07, Amendment 

39–14184 (70 FR 39647, July 11, 2005)].

12 work-hours × $85 

per hour = $1,020.

None .......................... $1,020 per airplane .... Up to $99,960. 

ESTIMATED COSTS FOR NEW ACTIONS

Retained action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspection and functional check of outboard 

foreflap installation for all airplanes [new 

action].

3 work-hours × $85 

per hour = $255 per 

inspection cycle.

None .......................... $255, per inspection 

cycle.

$24,990, per inspection cycle. 

Replacement of carriage attach fitting on outboard foreflap for certain airplanes [new 

action].

2 work-hours × $85 

per hour = $170.

$18,000 ...................... $18,170 per airplane .. Up to $1,780,660. 

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 slider or sidewall 

rubstrips.

2 work-hours × $85 per 

hour = $170.

Up to $175 ......................... Up to $345. 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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. 


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(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 


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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 UnReplaced (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 


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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-AMOCRequests@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/ibrlocations.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 

SECURITIES AND EXCHANGE 

COMMISSION 

17 CFR Part 232 

[Release Nos. 33–9668; 34–73390; 39–2498; 

IC–31294] 

Adoption of Updated EDGAR Filer 

Manual 

AGENCY: Securities and Exchange 

Commission. 

ACTION: Final rule. 

SUMMARY: The Securities and Exchange 

Commission (the Commission) is 

adopting revisions to the Electronic Data 

Gathering, Analysis, and Retrieval 

System (EDGAR) Filer Manual and 

related rules to reflect updates to the 

EDGAR system. The updates are being 

made primarily to support the revision 

of the disclosure, reporting and offering 

process for asset-backed securities 

(ABS) to enhance transparency and 

better protect investors in the 

securitization market; system upgrade to 

be compatible with Internet Explorer 

(IE) version 8.0; revision of the N–SAR 

system requirements. The EDGAR 

system is scheduled to be upgraded to 

support this functionality on October 

20, 2014. 

DATES: Effective October 29, 2014. The 

incorporation by reference of the 

EDGAR Filer Manual is approved by the 

Director of the Federal Register as of 

October 29, 2014. 

FOR FURTHER INFORMATION CONTACT: In 

the Division of Corporation Finance, for 

questions concerning the revisions for 

asset-backed securities contact Heather 

Mackintosh at (202) 551–3600; and in 

the Office of Information Technology, 

contact Tammy Borkowski at (202) 551– 

7208. 

SUPPLEMENTARY INFORMATION: We are 

adopting an updated EDGAR Filer 


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