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the part’s TIS. The part numbers listed in 

Table 2 to paragraph (e)(2) of this AD are not 

eligible for installation on any helicopter. 

TABLE 2 TO PARAGRAPH (e) OF THIS

AD—PARTS TO BE REMOVED FROM

SERVICE

Part name P/N 

Rod and bushing assembly, M/R.6410–21090– 

011 

M/R blade .......................... 6415–20001– 

013, –014, or 

–015 

Pylon stabilizer .................. 6420–66201– 

010, –014, or 

–015 

M/R shaft assembly ........... 6435–20078– 

013 

Oil cooler and support assembly.6435–60050– 

043 

Pitch change link, rotary 

rudder.

65113–07100– 

046 

Spindle, M/R blade ............ S1510–23070–3 

(3) Within 20 hours TIS, and thereafter at 

intervals not to exceed 20 hours TIS, visually 

inspect each M/R servo and control arm 

assembly, P/N S1565–20421–10, –11, –041, 

or –043, and determine if there is any oil 

leaking from the M/R tandem servo housing 

assembly (servo housing), P/N S1565–20252– 

2. If there is any oil leaking from the servo 

housing, before further flight, replace the M/ 

R servo and control arm assembly. 

(4) Within 20 hours TIS or before reaching 

1,120 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 200 hours 

TIS or 12 months, whichever occurs first, 

ultrasonic (UT) inspect each M/R hub 

horizontal hinge pin (hinge pin), P/N S1510– 

23099–1 or P/N S1510–23099–001, for a 

crack in accordance with the 

Accomplishment Instructions, paragraphs 

2.A through 2.C, of Erickson Service Bulletin 

(SB) No. 64B10–3, Revision D, dated October 

15, 2007, except you are not required to 

contact Erickson nor send hinge pins to 

them. A non-destructive testing (NDT) UT 

Level I Special, Level II, or Level III inspector 

who is qualified under the guidelines 

established by ASNT SNT–TC–1A, ISO 9712, 

or an FAA-accepted equivalent qualification 

standard for NDT inspection and evaluation, 

must perform the UT inspection. 

(5) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, 

perform a fluorescent-magnetic particle 

inspection (MPI) of each second stage 

planetary plate assembly, P/N 6435–20231– 

016, for a crack. 

(6) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 650 hours 

TIS, perform an MPI of each M/R shaft, 

P/N 6435–20078–104, for a crack, paying 

particular attention to the lower spline area. 

(7) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 1,450 

hours TIS, perform an MPI of each M/R shaft, 

P/N 6435–20078–105, for a crack, paying 

particular attention to the lower spline area. 

(8) Within 150 hours TIS or before reaching 

3,375 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 3,375 

hours TIS, perform a fluorescent penetrant 

inspection of each housing lug on each servo 

housing, P/N S1565–20252–2, for a crack. 

(9) At each overhaul of the main gearbox 

assembly, P/N 6435–20400–053, –054, –058, 

–060, –062, –063, –064, –065, or –066, 

perform an MPI of the entire shaft of each 

M/R shaft assembly, P/N 6435–20078–014, 

–015, or –016, for a crack, paying particular 

attention to the rotating swashplate spherical 

bearing ball travel area, which is located 

approximately ten inches above the upper 

roller bearing journal shoulder. 

(10) If there is a crack in any part, before 

further flight, replace the cracked part. 

(11) At each overhaul of the damper 

assembly, P/N 6410–26200–042, replace the 

following parts with airworthy parts that 

have zero (0) hours TIS: 

(i) All Air Force-Navy Aeronautical 

Standard (AN), Aerospace Standard (AS), 

Military Standard (MS), and National 

Aerospace Standard (NAS) nuts, bolts, 

washers, and packings, except packing, P/N 

MS28775–011, installed on stud, P/N 

SHF111–11SN–12A; 

(ii) Lock washer, P/N SS5073–2; 

(iii) Nut, P/N SS5081–05; 

(iv) Felt seal, P/N S1510–26017; 

(v) Retaining ring, P/N UR106L; and 

(vi) Nut, P/N 6410–26214–101. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aerospace Engineer, Rotorcraft Certification 

Office, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5170; email 7-avs-asw170@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

Erickson Service Bulletin (SB) No. 64B 

General-1, Revision 19, dated September 15, 

2010, which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information 

identified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson/ 

Compliance Officer, 3100 Willow Springs Rd, 

PO Box 3247, Central Point, OR 97502, 

telephone (541) 664–5544, fax (541) 664– 

2312, email address 

cerickson@ericksonaircrane.com. You may 

review a copy of this information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200: Main Rotor System; 6300: Main 

Rotor Drive System; 6410: Tail Rotor Blades; 

6500: Tail Rotor Drive System. 

Issued in Fort Worth, Texas, on May 17, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–12523 Filed 5–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0425; Directorate 

Identifier 2012–NM–224–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 adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747 

airplanes. This proposed AD was 

prompted by reports of cracking in the 

forward and aft inner chord of the body 

station (BS) 2598 bulkhead near the 

upper corners of the cutout for the 

horizontal stabilizer rear spar, and 

cracking in the bulkhead upper and 

lower web panels near the inner chord 

to shear deck connection. This proposed 

AD would require doing repetitive 

inspections for cracking in the bulkhead 

splice fitting, frame supports, forward 

and aft inner chords, and floor support; 

doing an inspection for cracking in the 

bulkhead upper web, doubler, and 

bulkhead lower web; and corrective 

actions if necessary; for certain 

airplanes, inspections for cracking in 

the repaired area of the bulkhead, and 

corrective actions if necessary; for 

certain airplanes, support frame 

modification and support frame 

inspections, and related investigative 

and corrective actions, if necessary; for 

certain airplanes, repetitive support 

frame post-modification inspections and 

inspections for cracking in the hinge 

support, and related investigative and 

corrective actions if necessary; for 

certain airplanes, a one-time inspection 

of the frame web and upper shear deck 

(floor support) chord aft side for 

fasteners; and a one-time inspection of 

the upper forward inner chord, frame 

support fitting and splice fitting, for the 

installation of certain fasteners; and 

related investigative and corrective 

actions if necessary; for certain 

airplanes, a one-time inspection of the 

upper forward inner chord, frame 


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support fitting and splice fitting for the 

installation of certain fasteners; a onetime inspection for any repair installed 

on the left and right side of the aft inner 

chord, and related investigative and 

corrective actions, if necessary; for 

certain airplanes, a one-time inspection 

of the support frame outer chord for 

cracking, and repair if necessary; and 

repetitive support frame post-repair 

inspections, and corrective actions, if 

necessary. We are proposing this AD to 

detect and correct fatigue cracking of the 

BS 2598 bulkhead structure, which 

could adversely affect the structural 

integrity of the bulkhead and the 

horizontal stabilizer support structure 

and result in loss of controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by July 12, 2013. 

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 

review copies of the 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; 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917– 

6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0425; Directorate Identifier 2012– 

NM–224–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 

We received reports of cracking in the 

forward and aft inner chord of the BS 

2598 bulkhead near the upper corners of 

the cutout for the horizontal stabilizer 

rear spar, and cracking in the bulkhead 

upper and lower web panels near the 

inner chord to shear deck connection. 

This condition, if not corrected, could 

result in fatigue cracking of the BS 2598 

bulkhead structure, which could result 

in inability of the structure to carry 

horizontal stabilizer flight loads, and 

loss of controllability of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–53A2427, Revision 6, 

dated July 14, 2011; and Boeing Alert 

Service Bulletin 747–53A2473, Revision 

4, dated December 1, 2011. For 

information on the procedures and 

compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0425. 

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 require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

The phrase ‘‘related investigative 

actions’’ might be used in this proposed 

AD. ‘‘Related investigative actions’’ are 

follow-on actions that: (1) Are related to 

the primary actions, and (2) are actions 

that further investigate the nature of any 

condition found. Related investigative 

actions in an AD could include, for 

example, inspections. 

In addition, the phrase ‘‘corrective 

actions’’ might be 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. 

Differences Between the Proposed AD 

and the Service Information 

Where Part 1 of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 747–53A2427, Revision 6, 

dated July 14, 2011, specifies 

accomplishing inspections for cracks in 

forward and aft inner chords, splice 

fittings, floor supports, and upper and 

lower web panels, this AD also requires 

doing an open-hole high frequency eddy 

current (HFEC) inspection of the 

doubler. Figure 2 of Boeing Alert 

Service Bulletin 747–53A2427, Revision 

6, dated July 14, 2011, includes the 

inspections. 

Where paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 747– 

53A2427, Revision 6, dated July 14, 

2011; or 747–53A2473, Revision 4, 

dated December 1, 2011; specify to 

contact Boeing for repair data and do 

the repair, this AD requires doing those 

repairs in accordance with a method 

approved by the FAA. 

If cracking is found in any doubler 

during any inspection specified by 

paragraph (g) of this proposed AD, this 

proposed AD would require repairing 

using a method approved in accordance 

with the procedures specified in 

paragraph (o) of this AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 165 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ...................................... 24 work-hours × $85 per hour = 

$2,040 per inspection cycle.

$0 $2,040 per inspection cycle.$336,600 per inspection cycle. 

Support frame modification ........... 315 work-hours × $85 per hour = 

$26,775.

0 $26,775 ............ Up to $4,417,875. 

Support frame upper corner fastener inspection.16 work-hours × $85 per hour = 

$1,360.

0 $1,360 .............. Up to $224,400. 

Support frame post-modification 

inspection.

200 work hours × $85 per hour = 

$17,000.

0 $17,000 ............ $2,805,000. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed 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 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 this 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 adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2013–0425; Directorate Identifier 2012– 

NM–224–AD. 

(a) Comments Due Date 

We must receive comments by July 12, 

2013. 

(b) Affected ADs 

This AD affects AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010). 

(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, 747SR, and 

747SP series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–53A2427, Revision 6, 

dated July 14, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the forward and aft inner chord 

of the body station (BS) 2598 bulkhead near 

the upper corners of the cutout for the 

horizontal stabilizer rear spar, and cracking 

in the bulkhead upper and lower web panels 

near the inner chord to shear deck 

connection. We are issuing this AD to detect 

and correct fatigue cracking of the BS 2598 

bulkhead structure, which could adversely 

affect the structural integrity of the bulkhead 

and the horizontal stabilizer support 

structure and result in loss of controllability 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections of the Bulkhead (Support 

Frame) 

For airplanes on which the bulkhead 

(support frame) modification specified in 

Boeing Service Bulletin 747–53A2473 has 

not been accomplished: At the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 6, dated July 

14, 2011, except as provided by paragraph 

(m)(1), (m)(2), or (m)(3), as applicable, of this 

AD, do an open-hole and surface high 

frequency eddy current (HFEC) inspection for 

cracking in the bulkhead (support frame) 

which includes the bulkhead splice fitting, 

frame supports, forward and aft inner chords, 

and floor support; do a surface HFEC 

inspection for cracking in the bulkhead 

upper web and doubler; do an open-hole and 

surface HFEC inspection for cracking in the 

bulkhead lower web; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2427, Revision 6, 

dated July 14, 2011, except as required by 

paragraphs (m)(4), (m)(5) and (m)(6) of this 

AD, and except as provided by paragraph (h) 

of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

applicable inspections, thereafter, at the 

applicable times in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 6, dated July 

14, 2011. Doing the modification required by 

paragraph (j) of this AD terminates the 

repetitive inspections required by this 

paragraph. 

(h) Interim Modification 

For airplanes in groups 1 and 2 as 

identified in Boeing Alert Service Bulletin 

747–53A2427, Revision 6, dated July 14, 

2011, on which no cracking was found 

during any inspection required by paragraph 

(g) of this AD: At the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 6, dated July 14, 2011, except as 

provided by paragraph (m)(2) of this AD, do 

the interim modification, in accordance with 


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the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2427, 

Revision 6, dated July 14, 2011. Doing the 

interim modification terminates the 

repetitive inspection requirement of 

paragraph (g) of this AD in the area of the 

modification only. The repetitive inspections 

of the bulkhead lower web, as specified in 

paragraph (g) of this AD, must be done. If the 

aft inner chord repair or upper web repair 

specified in Boeing Alert Service Bulletin 

747–53A2427, Revision 6, dated July 14, 

2011, has been accomplished, an interim 

modification on the side of the airplane that 

has the repair is not required by this 

paragraph. 

(i) Post-Repair Inspection or Post-Interim 

Modification Inspection 

For airplanes on which an interim 

modification, or aft inner chord repair, or 

upper web repair has been done as specified 

in paragraph (g) or (h) of this AD: At the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 6, dated July 

14, 2011, except as specified in paragraph 

(m)(1), (m)(2), or (m)(3), as applicable, of this 

AD, do the actions specified in paragraph 

(i)(1) and (i)(2) of this AD, and all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2427, Revision 6, 

dated July 14, 2011, except as required by 

paragraph (m)(4) of this AD. Do all applicable 

corrective actions before further flight. 

Repeat the inspections thereafter at the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 6, dated July 

14, 2011. Doing the modification required by 

paragraph (j) of this AD terminates the 

repetitive inspections required by this 

paragraph. 

(1) Do forward side surface HFEC 

inspections for cracking of the bulkhead 

forward inner chord, splice fitting, and frame 

support. 

(2) Do surface and open-hole HFEC 

inspections for cracking in the repaired area 

of the bulkhead. 

(j) Bulkhead (Support Frame) Modification 

and Inspections 

For airplanes on which the bulkhead 

(support frame) modification specified in 

Boeing Alert Service Bulletin 747–53A2473, 

dated March 24, 2005; Revision 1, dated 

February 20, 2007; Revision 2, dated August 

28, 2009; Revision 3, dated July 14, 2011; or 

Revision 4, dated December 1, 2011, has not 

been done as of the effective date of this AD: 

At the applicable time in tables 2 and 3 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011, do the 

bulkhead (support frame) modification and 

inspections and all applicable related 

investigative and corrective actions; in 

accordance with steps 3.B.3., 3.B.4., and 

3.B.5. of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011, except 

as required by paragraph (m)(4) of this AD. 

Do all applicable related investigative and 

corrective actions before further flight. Doing 

the modification in this paragraph terminates 

the inspections required by paragraphs (g) 

and (i) of this AD. 

(k) Post Modification Inspections 

(1) For airplanes on which the bulkhead 

(support frame) modification has been done 

as specified in Boeing Service Bulletin 747– 

53A2473, dated March 24, 2005; Revision 1, 

dated February 20, 2007; Revision 2, dated 

August 28, 2009; Revision 3, dated July 14, 

2011; or Revision 4, dated December 1, 2011: 

Except as provided by paragraphs (m)(7) and 

(m)(8) of this AD, at the applicable time in 

tables 6, 7, 8, and 9 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011, do support frame post-modification 

inspections, and open-hole HFEC inspection 

for cracking in the hinge support, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, except as required 

by paragraph (m)(4). Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspections 

thereafter at the applicable times in tables 6, 

7, 8, and 9 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011. 

(2) For airplanes on which the support 

frame modification has been done as 

specified in Boeing Service Bulletin 747– 

53A2473, Revision 1, dated February 20, 

2007: Except as specified in paragraphs 

(m)(7) and (m)(8) of this AD, at the applicable 

time in tables 4 and 5 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011, do a one-time general visual inspection 

of the frame web and upper shear deck (floor 

support) chord aft side for fasteners that were 

installed as part of an inner chord repair 

removal; and a one-time general visual 

inspection of the upper forward inner chord, 

frame support fitting and splice fitting, for 

the installation of certain fasteners; and do 

all applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, except as required 

by paragraph (m)(4) of this AD. Do all 

applicable related investigative and 

corrective actions at the applicable times 

specified in tables 4 and 5 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011. 

(3) For airplanes on which the support 

frame modification has been done as 

specified in Boeing Service Bulletin 747– 

53A2473, dated March 24, 2005: Except as 

specified in paragraphs (m)(7) and (m)(8) of 

this AD, at the applicable time in tables 5 and 

10 of paragraph 1.E., ‘‘Compliance’’ of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, do a one-time 

general visual inspection of the upper 

forward inner chord, frame support fitting, 

and splice fitting for the installation of 

certain fasteners; a one-time general visual 

inspection for any repair installed on the left 

and right side of the aft inner chord; and do 

all applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, except as required 

by paragraph (m)(4) of this AD. Do all 

applicable related investigative and 

corrective actions at the applicable times 

specified in tables 5 and 10 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011. 

(4) For airplanes on which a postmodification inspection was done in 

accordance with paragraph 3.B.8. of Part 1 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 3, 

dated July 14, 2011: Except as required by 

paragraphs (m)(7) and (m)(8) of this AD, at 

the applicable time in table 11 of paragraph 

1.E., ‘‘Compliance’’ of Boeing Service 

Bulletin 747–53A2473, Revision 4, dated 

December 1, 2011, do a one-time surface 

HFEC inspection of the support frame outer 

chord for cracking, in accordance with Part 

1 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011. If any 

cracking is found, repair before further flight, 

using a method approved in accordance with 

the procedures specified in paragraph (o) of 

this AD. 

(l) Post-Modification Post-Repair Inspections 

For airplanes on which post-modification 

inspection cracks were repaired by doing the 

installation of an upper or lower corner postmodification web crack repair as specified in 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011: At the 

applicable times specified in tables 6 and 8 

of paragraph 1.E., ‘‘Compliance’’ of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, do a bulkhead 

(support frame) post-repair inspection, and 

do all applicable corrective actions, in 

accordance with paragraph a., b., or c. of Part 

4 of paragraph 3.B.8 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, as applicable, except as required by 

paragraph (m)(4) of this AD. Repeat the 

inspection, thereafter, at the applicable times 

specified in tables 6 and 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011. 

(m) Exceptions 

(1) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 6, dated July 14, 

2011, specifies a compliance time after the 

date on Revision 2 of this service bulletin, 

this AD requires compliance within the 

specified compliance time as of August 28, 

2001 (the effective date of AD 2001–15–03, 

Amendment 39–12337 (66 FR 38365, July 24, 

2001)). 

(2) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 6, dated July 14, 

2011, specifies a compliance time after the 

date on Revision 4 of this service bulletin, 

this AD requires compliance within the 

specified compliance time as of April 13, 

2006 (the effective date of AD 2006–05–06, 

Amendment 39–14503 (71 FR 12125, March 

9, 2006)). 


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Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Proposed Rules 31871 

(3) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 6, dated July 14, 

2011, specifies a compliance time after the 

date on Revision 6 of this service bulletin, 

this AD requires compliance within the 

specified compliance time ‘‘after the effective 

date of this AD.’’ 

(4) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2427, 

Revision 6, dated July 14, 2011; or Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011; specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (o) of this AD. 

(5) If, during any inspection required by 

paragraph (g) of this AD, any cracking is 

found in the doubler, before further flight, 

repair, using a method approved in 

accordance with the procedures specified in 

paragraph (o) of this AD. 

(6) Where Part 1 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2427, Revision 6, dated July 14, 

2011, specifies accomplishing inspections for 

cracks for forward and aft inner chords, 

splice fittings, floor supports, and upper and 

lower web panels, this AD also requires 

doing an open-hole HFEC inspection of the 

doubler. 

(7) Where Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, specifies a compliance time after the 

date on Revision 2 of the service bulletin, 

this AD requires compliance within the 

specified compliance time as of August 5, 

2010 (the effective date of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010)). 

(8) Where Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, specifies a compliance time after the 

date on Revision 3 or 4 of the service 

bulletin, this AD requires compliance within 

the specified compliance time ‘‘after the 

effective date of this AD.’’ 

(n) Terminating Action for Certain 

Requirements of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010) 

(1) Accomplishing the inspections, repairs, 

and modification in accordance with Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, is a terminating 

action for the corresponding inspections, 

repairs, and modification at the STA 2598 

support frame required by paragraphs (i), (j), 

(k)(1), (m), (n), (o), (p), (q), (r), (s), (t), (u), and 

(v) of AD 2010–14–07, Amendment 39–16352 

(75 FR 38001, July 1, 2010). When Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, specifies to contact 

Boeing for repair instructions, the repair 

instructions must be approved by the FAA in 

accordance with paragraph (o) of this AD. All 

provisions of AD 2010–14–07 that are not 

specifically referenced in this paragraph 

remain fully applicable and must be 

complied with. 

(2) Accomplishing the inspections, repairs 

and interim modification in accordance with 

Boeing Service Bulletin 747–53A2427, 

Revision 6, dated July 14, 2011, is a 

terminating action for the corresponding 

inspections, repairs and interim modification 

at the STA 2598 bulkhead required by 

paragraphs (i), (j), (o), (s), (t), (u), and (v) of 

AD 2010–14–07, Amendment 39–16352 (75 

FR 38001, July 1, 2010). When Boeing 

Service Bulletin 747–53A2427, Revision 6, 

dated July 14, 2011, specifies to contact 

Boeing for repair data, the repair data must 

be approved by the FAA in accordance with 

paragraph (o) of this AD. All provisions of 

AD 2010–14–07 that are not specifically 

reference in this paragraph remain fully 

applicable and must be complied with. 

(o) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, 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. 

(p) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@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 review copies of the 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 May 17, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–12618 Filed 5–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0282; Airspace 

Docket No. 13–AAL–3] 

Proposed Amendment of Class E 

Airspace; Gustavus, AK 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace at Gustavus 

Airport, Gustavus, AK. 

Decommissioning of the Gustavus 

Nondirectional Radio Beacon (NDB) has 

made this action necessary for the safety 

and management of Instrument Flight 

Rules (IFR) operations at the airport. 

This action also would adjust the 

geographic coordinates of the airport. 

DATES: Comments must be received on 

or before July 12, 2013. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590; 

telephone (202) 366–9826. You must 

identify FAA Docket No. FAA–2013– 

0282; Airspace Docket No. 13–AAL–3, 

at the beginning of your comments. You 

may also submit comments through the 

Internet at 

http://www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Eldon Taylor, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue SW., Renton, WA 98057; 

telephone (425) 203–4537. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA 

2013–0282 and Airspace Docket No. 13– 

AAL–3) and be submitted in triplicate to 

the Docket Management System (see 


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