20178 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 

Issued in Renton, Washington, on April 6, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–08465 Filed 4–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0828; Directorate 

Identifier 2014–NM–146–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) 2013–23– 

03, which applies to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, and 747SR series 

airplanes. AD 2013–23–03 currently 

requires doing a detailed inspection of 

certain attach fittings for a cylindrical 

defect and replacing if necessary. Since 

we issued AD 2013–23–03, we received 

a report that a machining defect was 

also found on some of the actuator 

assemblies inspected during 

manufacture. This defect could lead to 

fatigue cracking and subsequent 

fracture. For certain airplanes, this 

proposed AD would mandate new 

inspections of the inboard actuator 

attach fittings for machining defects, 

and overhaul or replacement, if 

necessary. This proposed AD would 

also limit the compliance time for doing 

the replacement for certain other 

airplanes. We are proposing this AD to 

detect and correct defective inboard 

actuator attach fittings which, combined 

with loss of the outboard actuator load 

path, could result in uncontrolled 

retraction of the outboard flap, damage 

to flight control systems, and 

consequent reduced controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by June 1, 2015. 

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 proposed 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, Washington. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0828. 

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–2015– 

0828; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@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–2015–0828; Directorate Identifier 

2014–NM–146–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 October 31, 2013, we issued AD 

2013–23–03, Amendment 39–17658 (78 

FR 68345, November 14, 2013), for 

certain The Boeing Company Model 

747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747– 

300, 747–400, 747–400D, 747–400F, and 

747SR series airplanes. AD 2013–23–03 

requires inspecting to determine the 

part number of the inboard actuator 

attach fittings of the outboard flap. For 

affected attach fittings, AD 2013–23–03 

requires doing a detailed inspection of 

the attach fittings for a cylindrical defect 

and replacing if necessary. As an option 

to the detailed inspection, AD 2013–23– 

03 allows replacement of affected attach 

fittings. AD 2013–23–03 resulted from a 

report of the fracture of an inboard 

actuator attach fitting of the outboard 

flap. An inspection of the attach fitting 

revealed that it was incorrectly 

machined with a cylindrical profile 

instead of a conical profile, resulting in 

reduced wall thickness. We issued AD 

2013–23–03 to detect and correct 

defective inboard actuator attach fittings 

which, combined with loss of the 

outboard actuator load path, could 

result in uncontrolled retraction of the 

outboard flap, damage to flight control 

systems, and consequent reduced 

controllability of the airplane. 

Actions Since AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013) Was Issued 

The preamble to AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013), specified that we 

considered the requirements ‘‘interim 

action.’’ AD 2013–23–03 explained that 

we might consider further rulemaking to 

require a minimum thickness inspection 

of inboard actuator attach fittings that 

are conically machined. Since we issued 

AD 2013–23–03, we received a report 

that a machining defect was also found 

on some of the actuator assemblies 

inspected during manufacture at the 

point where the tapered machining 

transitioned to the hemispherical 

machining at the top of the inner 

surface. Revised service information has 

been issued and, for certain airplanes, 

this proposed AD would mandate new 

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Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20179 

inspections of the inboard actuator 

attach fittings for machining defects, 

and overhaul or replacement, if 

necessary. This proposed AD would 

also limit the compliance time for doing 

the replacement, for certain other 

airplanes. 

Related Service Information Under 1 

CFR part 51 

We reviewed Boeing Alert Service 

Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. The service 

information describes procedures for 

new inspections of the inboard actuator 

attach fittings for machining defects, 

and overhaul or replacement, if 

necessary. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

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. 

Related AD 

This proposed AD is related to AD 

2005–20–18, Amendment 39–14312 (70 

FR 57740, October 4, 2005), for Model 

747–100, –200B, –200F, –200C, –100B, 

–300 series airplanes. AD 2005–20–18 

required nspecting and overhauling, 

replacing, or repairing (as applicable) 

the actuator attach fittings on the 

inboard and outboard flaps of the wing. 

The replacement was done in 

accordance with Boeing Service Bulletin 

747–57A2316. 

Proposed AD Requirements 

This proposed AD would retain all of 

the requirements of AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013). For certain 

airplanes, this proposed AD would 

mandate new inspections of the inboard 

actuator attach fittings for machining 

defects, and overhaul or replacement, if 

necessary. This proposed AD would 

also limit the compliance time for doing 

the replacement for certain other 

airplanes. This proposed AD would also 

require accomplishing the actions 

specified in the service information 

described previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 184 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Retained inspection for part number in AD 

2013–23–03, Amendment 39–17658 (78 FR 

68345, November 14, 2013).

7 work-hours × $85 per hour = 

$595.

$0 $595 $109,480. 

New proposed inspections for machining defect.8 work-hours × $85 per hour = 

$680.

0 680 125,120. 

Replacement for airplanes without any defect .. 6 work-hours × $85 per hour = 

$510.

13,720 14,230 14,230 per airplane. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this AD. 

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 

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) 

2013–23–03, Amendment 39–17658 (78 

FR 68345, November 14, 2013), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2015–0828; Directorate Identifier 2014– 

NM–146–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by June 1, 2015. 

(b) Affected ADs 

This AD replaces AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013). 

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20180 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, and 747SR 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report of the 

fracture of an inboard actuator attach fitting 

of the outboard flap. An inspection of the 

attach fitting revealed that it was incorrectly 

machined with a cylindrical profile instead 

of a conical profile, resulting in reduced wall 

thickness. A machining defect was also 

found on some actuator assemblies inspected 

during manufacture at the point where the 

tapered machining transitioned to the 

hemispherical machining at the top of the 

inner surface. This defect could lead to 

fatigue cracking and subsequent fracture. We 

are issuing this AD to detect and correct 

defective inboard actuator attach fittings 

which, combined with loss of the outboard 

actuator load path, could result in 

uncontrolled retraction of the outboard flap, 

damage to flight control systems, and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Part Number Inspection 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013), with revised service 

information. Within 90 days after November 

29, 2013 (the effective date of AD 2013–23– 

03): Inspect to determine the part number of 

the inboard actuator attach fittings of the 

outboard flaps, in accordance with Part 1 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2343, dated 

September 12, 2013; or Boeing Alert Service 

Bulletin 747–57A2343, Revision 1, dated 

June 23, 2014. As of the effective date of this 

AD, only Boeing Alert Service Bulletin 747– 

57A2343, Revision 1, dated June 23, 2014, 

may be used. 

(h) Retained Actions for Certain Attach 

Fittings 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013), with revised service 

information. If, during the inspection 

required by paragraph (g) of this AD, any 

inboard actuator attach fitting having part 

number (P/N) 65B08564–7 is found, before 

further flight, do the actions specified in 

paragraph (h)(1) or (h)(2) of this AD. 

(1) Do a detailed inspection of the inboard 

actuator attach fitting for a cylindrical defect, 

in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, dated 

September 12, 2013; or Boeing Alert Service 

Bulletin 747–57A2343, Revision 1, dated 

June 23, 2014. As of the effective date of this 

AD, only Boeing Alert Service Bulletin 747– 

57A2343, Revision 1, dated June 23, 2014, 

may be used. For airplanes on which the 

detailed inspection is done before the 

effective date of this AD: If any cylindrical 

defect is found, before further flight, do the 

actions specified in paragraph (h)(1)(i) or 

(h)(1)(ii) of this AD. 

(i) Do a minimum thickness inspection of 

the inboard actuator attach fitting to 

determine minimum wall thickness of the 

actuator fitting assembly, in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2343, 

dated September 12, 2013; or Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. If the minimum 

thickness of the wall is less than 0.130 inch: 

Before further flight, replace the inboard 

actuator attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747 57A2343, dated 

September 12, 2013. 

(ii) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, dated September 12, 2013. 

(2) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, dated September 12, 2013. 

(i) New Actions For Certain Airplanes on 

Which Any Cylindrical Defect Is Found 

For airplanes on which the detailed 

inspection required by paragraph (h)(1) of 

this AD is done on or after the effective date 

of this AD: If any cylindrical defect is found 

during any inspection required by paragraph 

(h)(1) of this AD, before further flight, do the 

actions specified in paragraph (i)(1) or (i)(2) 

of this AD. 

(1) Determine the minimum wall thickness 

of the actuator attach fitting either by doing 

an ultrasonic inspection or by mechanically 

measuring the thickness and do a detailed 

inspection of the inner conical section to 

determine if the machining defect is present, 

in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(i) If the minimum thickness of the wall is 

less than 0.130 inch: Before further flight, 

replace the inboard actuator attach fitting of 

the outboard flap, in accordance with Part 4 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2343, 

Revision 1, dated June 23, 2014. 

(ii) If the minimum thickness of the wall 

is 0.140 inch or greater and the machining 

defect is present, before further flight, do the 

actions specified in paragraph (i)(1)(ii)(A) or 

(i)(1)(ii)(B) of this AD. 

(A) Overhaul the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(B) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(iii) If the minimum thickness of the wall 

is 0.130 inch or greater and less than 0.140 

inch and the machining defect is not present, 

within 48 months or 3,000 flight cycles after 

the effective date of this AD, whichever 

occurs first, replace the inboard actuator 

attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(iv) If the minimum thickness of the wall 

is 0.130 inch or greater and less than 0.140 

inch and the machining defect is present, 

before further flight, replace the inboard 

actuator attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(2) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(j) New Actions for Airplanes on Which No 

Cylindrical Defects Are Found 

If no cylindrical defect is found during any 

inspection required by paragraph (h)(1) of 

this AD, within 24 months after the effective 

date of this AD, do the actions specified in 

paragraph (j)(1) or (j)(2) of this AD. 

(1) Determine the minimum wall thickness 

of the actuator attach fitting either by doing 

an ultrasonic inspection or by mechanically 

measuring the thickness and do a detailed 

inspection of the inner conical section to 

determine if the machining defect is present, 

in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(i) If the minimum thickness of the wall is 

less than 0.130 inch: Before further flight, 

replace the inboard actuator attach fitting of 

the outboard flap, in accordance with Part 4 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747 57A2343, 

Revision 1, dated June 23, 2014. 

(ii) If the minimum thickness of the wall 

is 0.140 inch or greater and the machining 

defect is present, before further flight, do the 

actions specified in paragraph (j)(1)(ii)(A) or 

(j)(1)(ii)(B) of this AD. 

(A) Overhaul the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(B) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

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Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20181 

(iii) If the minimum thickness of the wall 

is 0.130 inch or greater and less than 0.140 

inch and the machining defect is not present, 

within 48 months or 3,000 flight cycles after 

the effective date of this AD, whichever 

occurs first, replace the inboard actuator 

attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(iv) If the minimum thickness of the wall 

is 0.130 inch or greater and less than 0.140 

inch and the machining defect is present, 

before further flight, replace the inboard 

actuator attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(2) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(k) New Inspection or Replacement for 

Certain Fittings That Were Previously 

Inspected 

For airplanes with any inboard actuator 

attach fitting having P/N 65B08564–7 

installed and the fitting was inspected in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, dated 

September 12, 2013: Within 24 months after 

the effective date of this AD, do the actions 

specified in paragraph (k)(1) or (k)(2) of this 

AD. 

(1) Do a detailed inspection of the inner 

conical section for machining defects only, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(i) If any machining defect is found and the 

minimum thickness of the wall is 0.140 inch 

or greater: Before further flight, do the actions 

specified in paragraph (k)(1)(i)(A) or 

(k)(1)(i)(B) of this AD. 

(A) Overhaul the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(B) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(ii) If any machining defect is found and 

the minimum thickness of the wall is 0.130 

inch or greater and less than 0.140 inch: 

Before further flight, replace the inboard 

actuator attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(iii) If no machining defect is found and 

the minimum thickness of the wall is 0.130 

inch or greater and less than 0.140 inch: 

Within 48 months or 3,000 flight cycles after 

the effective date of this AD, whichever 

occurs first, replace the inboard actuator 

attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, Revision 1, 

dated June 23, 2014. 

(iv) If a machining defect is or is not found 

and the minimum thickness of the wall is 

less than 0.130 inch: Before further flight, 

replace the inboard actuator attach fitting of 

the outboard flap, in accordance with Part 4 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2343, 

Revision 1, dated June 23, 2014. 

(2) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, Revision 1, dated June 23, 

2014. 

(l) Part Installation Limitation 

As of the effective date of this AD, no 

actuator attach fitting having P/N 65B08564– 

7 that meets the requirements of CONDITION 

5 or CONDITION 6 defined in Boeing Alert 

Service Bulletin 747–57A2343, dated 

September 12, 2013, may be installed on any 

airplane unless the inspection specified in 

paragraph (k)(1) of this AD is done and the 

applicable actions in paragraphs (k)(1)(i), 

(k)(1)(ii), (k)(1)(iii), and (k)(1)(iv) are done 

within the applicable times specified in 

paragraphs (k)(1)(i), (k)(1)(ii), (k)(1)(iii), and 

(k)(1)(iv) of this AD. 

(m) 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 (n)(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 any service information contains 

steps that are identified as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

identified as RC are recommended. Those 

steps that are not identified as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC provided the steps 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC require approval of an 

AMOC. 

(5) AMOCs approved for AD 2013–23–03, 

Amendment 39–17658 (78 FR 68345, 

November 14, 2013) are approved as AMOCs 

for the corresponding provisions of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@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, Washington. 

For information on the availability of this 

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

Issued in Renton, Washington, on April 6, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–08464 Filed 4–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0827; Directorate 

Identifier 2014–NM–008–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2011–07– 

10, for certain Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) 

airplanes. AD 2011–07–10 currently 

requires revising the Airworthiness 

Limitations section of the Instructions 

for Continued Airworthiness; doing 

detailed visual inspections; removing 

discrepant material; cleaning the 

surfaces of the valves, the plug of the 

sensing port, and the cabin pressuresensing port plug; securing the 

insulation; installing a new safety valve, 

mstockstill on DSK4VPTVN1PROD with PROPOSALS