Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Proposed Rules 16241 

(a) Comments Due Date 

We must receive comments by May 9, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Dassault Aviation 

Model FALCON 7X airplanes, certificated in 

any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Main Landing Gear. 

(e) Reason 

This AD was prompted by reports that the 

pintle pins installed on a certain number of 

airplanes may be incorrectly protected 

against corrosion. We are issuing this AD to 

detect and correct pintle pins that have been 

incorrectly corrosion-protected, which could 

cause the pintle pins to shear under normal 

load and lead to the collapse of the MLG 

during take-off or landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

For airplanes having serial numbers 4 

through 6 inclusive; 9, 12, 19, 21 through 25 

inclusive; 29, 32, 33, 37, 39 through 42 

inclusive; 45, 49 through 53 inclusive; 55, 56, 

62, 63, 65, 67 through 69 inclusive; and 81, 

82, 84, and 120: Within 2 months after the 

effective date of this AD, replace the pintle 

pins having part number (P/N) 55–2355007– 

01 on the left- and right-hand MLG with a 

serviceable part, in accordance with the 

Accomplishment Instructions of Dassault 

Aviation Mandatory Service Bulletin 7X–182, 

Revision 4, dated July 18, 2013. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a pintle pin having P/N 

55–2355007–01, with the following serial 

numbers, on any airplane: EXC–0001, EXC– 

0003, EXC–0008, EXC–0009, EXC–0010, 

EXC–0015, EXC–0017, EXC–0018, EXC– 

0019, EXC–0020, EXC–0022, EXC–0023, 

EXC–0024, EXC–0025, EXC–0026, EXC– 

0027, EXC–0029, EXC–0030, EXC–0031, 

EXC–0033, EXC–0037, EXC–0038, EXC– 

0040, EXC–0041, EXC–0043, EXC–0044, 

EXC–0045, EXC–0046, EXC–0047, EXC– 

0050, EXC–0051, EXC–0052, EXC–0053, 

EXC–0054, EXC–0057, EXC–0059, EXC– 

0060, EXC–0061, EXC–0062, EXC–0063, 

EXC–0064, EXC–0065, EXC–0067, EXC– 

0069, EXC–0072, EXC–0074, EXC–0075, 

EXC–0076, EXC–0077, EXC–0078, EXC– 

0084, EXC–0091, EXC–0092, EXC–0093, 

EXC–0096, EXC–0098, EXC–0099, EXC– 

0101, EXC–0102, EXC–0103, EXC–0106, 

EXC–0107, EXC–0108, EXC–0109, EXC– 

0110, EXC–0111, EXC–0114, EXC–0115, 

EXC–0117, EXC–0119, EXC–0120, EXC– 

0121, EXC–0122, EXC–0123, EXC–0124, 

EXC–0125, EXC–0126, EXC–0127, EXC– 

0128, EXC–0129, EXC–0130, EXC–0131, 

EXC–0132, EXC–0133, EXC–0134, EXC– 

0135, EXC–0136, EXC–0137, EXC–0138, 

EXC–0139, EXC–0143, EXC–0144, EXC– 

0147, EXC–0148, EXC–0149, EXC–0150, 

EXC–0152, EXC–0153, EXC–0154, EXC– 

0155, EXC–0158, EXC–0162, EXC–0163, 

EXC–0164, EXC–0167, EXC–0168, EXC– 

0170, EXC–0172, EXC–0173, EXC–0175, 

EXC–0177, EXC–0178, EXC–0183, EXC– 

0184, EXC–0190, EXC–0192, EXC–0193, 

EXC–0194, EXC–0197, EXC–0198. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using the following service 

information: 

(1) Dassault Aviation Service Bulletin 7X– 

182, dated December 17, 2010. 

(2) Dassault Aviation Service Bulletin 7X– 

182, Revision 1, dated December 7, 2011. 

(3) Dassault Aviation Service Bulletin 7X– 

182, Revision 2, dated June 1, 2012. 

(4) Dassault Aviation Service Bulletin 7X– 

182, Revision 3, dated February 26, 2013. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 227–1137; fax: (425) 227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the DAH with a 

State of Design Authority’s design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) issued 

EASA Airworthiness Directive 2013–0162, 

dated July 24, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating it in Docket No. 

FAA–2014–0145. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.com. You may view this 

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 March 

17, 2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–06492 Filed 3–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0170; Directorate 

Identifier 2013–NM–169–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) 2005–13– 

05, which applies to certain Boeing 

Model 747–400F series airplanes. AD 

2005–13–05 currently requires 

inspections for cracking of the web, 

upper chord, and upper chord strap of 

the upper deck floor beams, and repair 

of any cracking. AD 2005–13–05 also 

requires a preventive modification of 

the upper deck floor beams, and 

repetitive inspections for cracking after 

accomplishing the modification. Since 

we issued AD 2005–13–05, the upper 

chords of the upper deck floor beams at 

certain stations have been determined to 

be structures that are susceptible to 

widespread fatigue damage, and certain 

airplanes with an initial modification 

require a second modification for the 

airplane to meet its limit of validity 

(LOV). This proposed AD would require 

that second modification and repetitive 

inspections for cracking and repair if 

necessary. We are proposing this AD to 

detect and correct fatigue cracking in 

certain upper chords of the upper deck 

floor beam, which could result in 

reduced structural integrity of the 

airplane and rapid decompression or 

reduced controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 9, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 


tkelley on DSK3SPTVN1PROD with PROPOSALS
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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, 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– 

0170; 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 

(ACO), 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–2014–0170; Directorate Identifier 

2013–NM–169–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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as widespread fatigue 

damage (WFD). As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

design approval holders (DAHs) 

establish LOV of the engineering data 

that support the structural maintenance 

program. Operators affected by the WFD 

rule may not fly an airplane beyond its 

LOV, unless an extended LOV is 

approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

On June 10, 2005, we issued AD 

2005–13–05, Amendment 39–14141 (70 

FR 35989, June 22, 2005) for certain 

Boeing Model 747–400F series 

airplanes. AD 2005–13–05 requires 

initial detailed and open-hole high 

frequency eddy current inspections for 

cracking of the web, upper chord, and 

upper chord strap of the upper deck 

floor beams, and repair of any cracking. 

AD 2005–13–05 also requires a 

preventive modification of the upper 

deck floor beams, and repetitive 

inspections for cracking after 

accomplishing the modification. AD 

2005–13–05 resulted from reports of 

fatigue cracking found on the upper 

deck floor beam to frame attachment 

points. We issued AD 2005–13–05 to 

prevent fatigue cracks in the upper 

chord, upper chord strap, and the web 

of the upper deck floor beams and 

resultant failure of the floor beams. 

Actions Since AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, 

June 22, 2005) Was Issued 

Since we issued AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, 

June 22, 2005), we received reports that 

indicate that the upper chords of the 

upper deck floor beams at stations 

(STA) 340 through 520 have been 

determined to be structures that are 

susceptible to widespread fatigue 

damage, and airplanes that had an 

initial modification done before 15,000 

total flight cycles require a second 

fastener hole zero-timing modification 

for the airplane to meet its LOV. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

747–53A2443, Revision 2, dated August 

2, 2013. For information on the 

procedures and compliance times, see 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Proposed Rules 16243 

this service information at http://

www.regulations.gov by searching for 

Docket No. FAA–2014–0170. 

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 of 

the requirements of AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, 

June 22, 2005). This proposed AD 

would also require accomplishing the 

actions specified in the service 

information described previously. 

Difference Between This Proposed AD 

and Service Information 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Explanation of Compliance Time 

The compliance time for the 

modification specified in this proposed 

AD for addressing WFD was established 

to ensure that discrepant structure is 

modified before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. We will not grant any extensions 

of the compliance time to complete any 

AD-mandated service bulletin related to 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 13 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 

Pre-modification inspections [retained actions from AD 

2005–13–05, Amendment 39–14141 (70 FR 35989, 

June 22, 2005).

11 work-hours × $85 per 

hour = $935.

$0 ............................ $935 $12,155. 

Modification/inspections done during modification [retained 

actions from AD 2005-13–05, Amendment 39–14141 

(70 FR 35989, June 22, 2005).

Up to 524 work-hours × $85 

per hour = $44,540.

Up to 14,874 ........... 59,414 772,382. 

Post-modification inspections [retained actions from AD 

2005–13–05, Amendment 39–14141 (70 FR 35989, 

June 22, 2005).

66 work-hours × $85 per 

hour = $5,610.

0 .............................. 5,610 72,930. 

Zero-Timing Procedure Option 1 (including inspections) 

(proposed action).

71 work-hours × $85 per 

hour = $6,035.

0 .............................. 6,035 Up to 78,455. 

Zero-Timing Procedure Option 2 (including inspections) 

(proposed action).

103 work-hours × $85 per 

hour = $8,755.

0 .............................. 8,755 Up to 

113,815. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

products that may need these actions. 

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. Amend § 39.13 by removing 

Airworthiness Directive (AD) 2005–13– 

05, Amendment 39–14141 (70 FR 

35989, June 22, 2005), and adding the 

following new AD: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
16244 Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Proposed Rules 

The Boeing Company: Docket No. FAA– 

2014–0170; Directorate Identifier 2013– 

NM–169–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by May 9, 2014. 

(b) Affected ADs 

This AD supersedes AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400F series airplanes, certificated 

in any category, as identified in Boeing 

Service Bulletin 747–53A2443, Revision 2, 

dated August 2, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that the upper chords of the upper 

deck floor floor beams at stations (STA) 340 

through 520 have been determined to be 

structures that are susceptible to widespread 

fatigue damage, and airplanes that had an 

initial modification done before 15,000 total 

flight cycles require a second fastener hole 

zero-timing modification for the airplane to 

meet its limit of validity (LOV). We are 

issuing this AD to detect and correct fatigue 

cracking in certain upper chords of the upper 

deck floor beam, which could result in 

reduced structural integrity of the airplane 

and rapid decompression or reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005), with revised service information. 

Before the accumulation of 15,000 total flight 

cycles, or within 1,000 flight cycles after July 

27, 2005 (the effective date of AD 2005–13– 

05 whichever is later: Accomplish detailed 

and open-hole high frequency eddy current 

(HFEC) inspections for cracking of the web, 

upper chord, and upper chord strap of the 

upper deck floor beams, by doing all the 

applicable actions in accordance with Part 

3.B.1. of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, dated 

May 9, 2002; or Part 1 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, Revision 2, 

dated August 2, 2013. As of the effective date 

of this AD, only Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013, 

may be used. 

(h) Retained Repair With Revised Service 

Information and Revised Repair Approval 

Language 

This paragraph restates the requirements of 

paragraph (h) of AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005), with revised service information 

and revised repair approval language. If any 

crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, accomplish the actions 

required by paragraph (h)(1) and (h)(2) of this 

AD. 

(1) Repair in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013; 

except where these service bulletins specify 

to contact Boeing for appropriate action, 

before further flight, repair the cracking using 

a method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD. After the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(2) Accomplish the inspections and 

preventive modification of the floor beams by 

doing all the actions in accordance with Part 

3.B.2. or Part 3.B.3., as applicable, of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002, or Part 2 or Part 3 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, Revision 2, 

dated August 2, 2013. If any crack is found 

during any inspection, before further flight, 

repair as required by paragraph (h)(1) of this 

AD. After the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(i) Retained Modification With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2005–13–05, Amendment 

39–14141 (70 FR 35989, June 22, 2005), with 

revised service information. If no crack is 

found during any inspection required by 

paragraph (g) of this AD: Accomplish the 

actions required by either paragraph (i)(1) or 

(i)(2) of this AD, at the time specified. 

(1) Before further flight: Accomplish the 

inspections and preventive modification of 

the floor beam by doing all the actions in 

accordance with Part 3.B.2 or Part 3.B.3., as 

applicable, of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, dated May 9, 2002; or Part 2 or Part 

3 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013. If the 

preventive modification is performed 

concurrently with the inspections required 

by paragraph (g) of this AD, the upper chord 

straps must be removed when performing the 

open-hole HFEC inspection. If any crack is 

found during any inspection, before further 

flight, repair as required by paragraph (h)(1) 

of this AD. After the effective date of this AD, 

only Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(2) Before the accumulation of 20,000 total 

flight cycles, or within 1,000 flight cycles 

after July 27, 2005 (the effective date of AD 

2005–13–05, Amendment 39–14141 (70 FR 

35989, June 22, 2005), whichever is later: 

Accomplish the inspections and preventive 

modification of the upper deck floor beams, 

by doing all the actions in accordance with 

Part 3.B.2. or 3.B.3. as applicable, of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or Part 2 or Part 3, as applicable, of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, Revision 2, 

dated August 2, 2013. If any crack is found 

during any inspection, before further flight, 

repair as required by paragraph (h)(1) of this 

AD. After the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(j) Retained Post-Modification Inspections 

With Revised Service Information 

This paragraph restates the requirements of 

paragraph (j) of AD 2005–13–05, Amendment 

39–14141 (70 FR 35989, June 22, 2005), with 

revised service information. Within 15,000 

flight cycles after accomplishing the 

applicable preventive modification required 

by paragraph (h)(2), (i)(1), or (i)(2) of this AD: 

Accomplish the inspections required by 

either paragraph (j)(1) or (j)(2) of this AD; if 

any crack is found during any inspection, 

before further flight, repair as required by 

paragraph (h)(1) of this AD. 

(1) Accomplish detailed and surface HFEC 

inspections for cracking of the web, upper 

chord, and upper chord strap of the upper 

deck floor beams, by doing all the applicable 

actions in accordance with Part 3.B.4. of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or Part 4 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013. 

If no crack is found, repeat the inspections 

at intervals not to exceed 1,000 flight cycles. 

After the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(2) Accomplish detailed and open-hole 

HFEC inspections for cracking of the web, 

upper chord, and strap of the upper deck 

floor beams, by doing all the applicable 

actions in accordance with Part 3.B.5. of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or Part 5 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013. 

If no crack is found, repeat the inspections 

at intervals not to exceed 5,000 flight cycles. 

After the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(k) New Floor Beam Hole Zero-Timing 

Within 20,000 flight cycles after 

accomplishing the preventive modification of 

the Station 340 to Station 520 upper deck 

floor beams specified in paragraph (h)(2), 

(i)(1), or (i)(2) of this AD, or within 1,000 

flight cycles after the effective date of this 

AD, whichever occurs later: Accomplish the 

floor beam hole zero-timing in accordance 

with Part 6. of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Proposed Rules 16245 

(l) New Post-Floor Beam Hole Zero-Timing 

Inspections 

Within 15,000 flight cycles after 

accomplishing the floor beam hole zerotiming required by paragraph (k) of this AD: 

Accomplish the inspections required by 

either paragraph (l)(1) or (l)(2) of this AD; if 

any cracking is found during any inspection, 

before further flight, repair as required by 

paragraph (h)(1) of this AD. 

(1) Accomplish detailed and surface HFEC 

inspections for cracking of the web, upper 

chord, and straps of the Station 340 to 

Station 520 upper deck floor beams, by doing 

all the applicable actions, in accordance with 

Part 4 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013. If no 

cracking is found, repeat the inspections at 

intervals not to exceed 1,000 flight cycles. 

(2) Accomplish detailed and open-hole 

HFEC inspections for cracking of the web, 

upper chord, and straps of the Station 340 to 

Station 520 upper deck floor beams, by doing 

all the applicable actions, in accordance with 

Part 5. of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013. If no 

cracking is found, repeat the inspections at 

intervals not to exceed 5,000 flight cycles. 

(m) Exception to Service Information 

Where Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013, 

specifies a compliance time ‘‘after the 

revision date on this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(n) Credit for Previous Actions 

This paragraph provides credit for the 

inspections, repairs, and modification 

required by paragraphs (g) through (j) of this 

AD, if the corresponding actions were 

performed before the effective date of this AD 

using Boeing Service Bulletin 747–53A2443, 

Revision 1, dated June 25, 2009. 

(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 

paragraph (p)(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 

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) AMOCs approved for AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005), are approved as AMOCs for the 

corresponding requirements of paragraphs (g) 

through (j) (the retained actions) of this AD. 

(p) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 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 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 March 

17, 2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–06494 Filed 3–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0144; Directorate 

Identifier 2013–NM–232–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 adopt a new 

airworthiness directive (AD) for certain 

Bombardier Model DHC–8–400, –401, 

and –402 airplanes. This proposed AD 

was prompted by reports of rudder 

bearings falling out of the fore rudder 

hinge bracket during assembly. This 

proposed AD would require a proof load 

test and detailed inspections; and 

installation of a new bearing, reaming, 

or repair of the bearing if necessary. We 

are proposing this AD to detect and 

correct improper bearing installation, 

which could result in abnormal wear 

and potential increased freeplay in the 

rudder system, and resultant airframe 

vibration, leading to compromise of the 

flutter margins of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 9, 2014. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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– 

0144; 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 Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7331; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


tkelley on DSK3SPTVN1PROD with PROPOSALS