Federal Register / Vol. 79, No. 131 / Wednesday, July 9, 2014 / Proposed Rules 38801 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2014–0429; Directorate Identifier 2014– 

NM–039–AD. 

(a) Comments Due Date 

We must receive comments by August 25, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 and 747–400F airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–25A3640, 

dated January 8, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the main equipment center (MEC) 

drip shield and exhaust plenum. We are 

issuing this AD to prevent water penetration 

into the MEC, which could result in an 

electrical short and potential loss of several 

functions essential for safe flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation 

Within 24 months after the effective date 

of this AD, install a fiberglass reinforcing 

overcoat on the MEC drip shield, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–25A3640, dated January 8, 2014. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (i)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-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, Seattle 

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) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(i) Related Information 

(1) For more information about this AD, 

Francis Smith, Aerospace Engineer, Cabin 

Safety and Environmental Systems Branch, 

ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone: 425– 

917–6596; fax: 425–917–6590; email: 

Francis.Smith@faa.gov. 

(2) 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 Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on June 26, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–16008 Filed 7–8–14; 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] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2005–14– 

07, which applies to certain The Boeing 

Company Model 727, 727C, 727–100, 

727–100C, 727–200, and 727–200F 

series airplanes. AD 2005–14–07 

currently requires 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. Since we issued AD 2005– 

14–07, we received a report of broken 

inboard and outboard carriage attach 

fittings of the outboard foreflaps found 

during an inspection. This proposed AD 

would reduce certain repetitive 

inspection intervals for the inboard and 

outboard carriage attach fittings for the 

outboard foreflaps, require previously 

optional terminating actions which 

install improved outboard foreflap 

carriage attach fittings, and add new 

initial and repetitive inspections of 

those fittings and corrective actions if 

necessary. We are proposing 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: We must receive comments on 

this proposed AD by August 25, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 


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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 Airplane 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0431; Directorate Identifier 

2013–NM–041–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 29, 2005, we issued AD 

2005–14–07, Amendment 39–14184 (70 

FR 39647, July 11, 2005), for certain 

Boeing Model 727, 727C, 727–100, 727– 

100C, 727–200, and 727–200F series 

airplanes. AD 2005–14–07 requires 

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. For 

certain airplanes, AD 2005–14–07 also 

concurrently requires various other 

actions related to the subject area. AD 

2005–14–07 also provides for an 

optional terminating action for the 

repetitive inspection requirements and 

for an optional replacement that defers 

the repetitive inspections. AD 2005–14– 

07 resulted from reports of damaged or 

failed outboard foreflaps with a cracked 

or failed carriage attach fitting of the 

foreflap sequencing carriage. We issued 

AD 2005–14–07 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. 

Actions Since AD 2005–14–07, 

Amendment 39–14184 (70 FR 39647, 

July 11, 2005) Was Issued 

Since we issued AD 2005–14–07, 

Amendment 39–14184 (70 FR 39647, 

July 11, 2005), we received 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. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 727–57A0135, Revision 4, 

dated September 26, 2012. For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2014–0431. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2005–14–07, 

Amendment 39–14184 (70 FR 39647, 

July 11, 2005). This proposed AD would 

reduce certain repetitive inspection 

intervals for the inboard and outboard 

carriage attach fittings of the outboard 

foreflaps, require previously optional 

terminating actions which install 

improved outboard foreflap carriage 

attach fittings, and add new initial and 

repetitive inspections of those fittings 

and corrective action if necessary. This 

proposed AD would also require 

accomplishing the actions specified in 

the service information described 

previously. This proposed AD would 

also add a reference to Figure 3 of 

Boeing Alert Service Bulletin 727– 

57A0135, Revision 3, dated June 27, 

2002, in paragraph (i)(2) of this 

proposed AD that restates the 

requirements of paragraph (i) of AD 

2005–14–07, to provide for further 

information on corrective actions. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Change to AD 2005–14–07, Amendment 

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

This proposed AD would retain all 

requirements of AD 2005–14–07, 

Amendment 39–14184 (70 FR 39647, 

July 11, 2005). Since AD 2005–14–07 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. As a result, the 

corresponding paragraph identifiers 

have been redesignated in this proposed 

AD, as listed in the following table: 

REVISED PARAGRAPH DESIGNATIONS

Requirement in 

AD 2005–14–07, 

Amendment 39– 

14184 (70 FR 39647, 

July 11, 2005) 

Corresponding 

requirement in this 

proposed AD 

paragraph (f) paragraph (g) 

paragraph (g) paragraph (h) 

paragraph (h) paragraph (i)(1) 

paragraph (i) paragraph (i)(2) 

paragraph (j) paragraph (j)(1) 

paragraph (k) paragraph (j)(2) 

paragraph (l) paragraph (j)(3) 

paragraph (m) paragraph (j)(4) 

paragraph (n) paragraph (k) 

paragraph (o) paragraph (l) 

paragraph (p) paragraph (r)(1) 

paragraph (q) paragraph (r)(2) 

Costs of Compliance 

We estimate that this proposed AD 

affects 98 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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RETAINED ESTIMATED COSTS

Retained action Work hours Parts cost Cost 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 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 $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 None ........ $340 per airplane ...... Up to $33,320. 

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

ESTIMATED COSTS FOR NEW PROPOSED ACTIONS

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 proposed 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 proposed 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 

proposed 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 proposed 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 22, 2005), and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2014–0431; Directorate Identifier 2013– 

NM–041–AD. 


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(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 25, 2014. 

(b) Affected ADs 

This AD supersedes 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. 

(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 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 Requirement for Crack or 

Surface Deviation Findings: 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 


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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 

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 Requirement of This AD: 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 Requirement of This AD: 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 Requirement of This AD: 

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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
38806 Federal Register / Vol. 79, No. 131 / Wednesday, July 9, 2014 / Proposed Rules 

(p) New Requirement of This AD: 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 

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 Requirement of This AD: 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 (u) 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) 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. 

Issued in Renton, Washington, on June 27, 

2014. 

John P. Piccola, 

Acting Manager, Transport Aircraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15986 Filed 7–8–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0437; Directorate 

Identifier: 2012–CE–036–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Piper Aircraft, 

Inc. Models PA–31P airplanes. AD 76– 

06–09 currently requires repetitive 

inspection of certain exhaust system 

parts with replacement of parts mating 

with the turbocharger, as necessary, and 

allows installation of a certain tailpipe 

v-band coupling as terminating action. 

Since we issued AD 76–06–09, there 

have been reports of exhaust system 

failures, the manufacturer issued new 

service information, and the tailpipe vband coupling used for terminating 

action is obsolete. This proposed AD 

would require the use of the new service 

information and expand the scope of the 

inspections of the turbocharger exhaust 

system. We are proposing this AD to 

correct the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by August 25, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, use the following contact 

information, as applicable, Piper 

Aircraft, Inc., 2926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 

567–4361; fax: (772) 978–6573; Internet: 

www.piper.com/home/pages/

Publications.cfm; or Lycoming Engines, 

652 Oliver Street, Williamsport, 

Pennsylvania 17701; telephone: (570) 


emcdonald on DSK67QTVN1PROD with PROPOSALS