Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations 40955 

Applicability 

(c) This AD applies to Boeing Model 747–

400 and 747–400D series airplanes, 

certificated in any category; as identified in 

Boeing Special Attention Service Bulletin 

747–24–2257, Revision 1, dated August 2, 

2007. 

Unsafe Condition 

(d) This AD results from a report that the 

power feeder wire bundle of the auxiliary 

power unit (APU) was found touching the 

hydraulic system return tube during 

inspection of an airplane. We are issuing this 

AD to prevent insufficient clearance between 

the wire bundle and hydraulic tube that 

could lead to chafing of the wire bundle, 

which could cause arcing and a consequent 

hydraulic fluid fire in an area outside of the 

smoke detection and fire extinguishing zone; 

this condition could result in an 

uncontrolled fire on the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection and Related Investigative and 

Corrective Actions 

(f) Within 24 months after the effective 

date of this AD, do a general visual 

inspection of the power feeder wire bundle 

of the APU where it crosses the hydraulic 

system 4 return tube to determine if parts are 

installed to provide separation between the 

wire bundle and hydraulic tube, and do all 

the related investigative and corrective 

actions as applicable, by accomplishing all of 

the actions specified in the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–24–2257, Revision 1, 

dated August 2, 2007. The related 

investigative and corrective actions must be 

accomplished before further flight after the 

inspection. 

Credit for Actions Done According to 

Previous Issue of Service Bulletin 

(g) Actions done before the effective date 

of this AD in accordance with Boeing Special 

Attention Service Bulletin 747–24–2257, 

dated May 18, 2006, are acceptable for 

compliance with the corresponding 

requirements of paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

Material Incorporated by Reference 

(i) You must use Boeing Special Attention 

Service Bulletin 747–24–2257, Revision 1, 

dated August 2, 2007, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on June 27, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–15710 Filed 7–16–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0362; Directorate 

Identifier 2007–NM–308–AD; Amendment 

39–15611; AD 2008–14–16] 

RIN 2120-AA64 

Airworthiness Directives; 328 Support 

Services GmbH Dornier Model 328–100 

and –300 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

At least one incident has occurred where, 

immediately after take-off, the passenger door 

of a Dornier 328 completely opened. * * * 

Substantial damage to the door, handrails, 

door hinge arms and fuselage skin were 

found. 

* * * Although final proof could not be 

obtained, the most likely way in which the 

door opened was that the door handle was 

inadvertently operated during the take-off 

run. 

* * * * * 

[T]his Airworthiness Directive (AD) aims 

to prevent further incidents of inadvertent 

opening and possible detachment of a 

passenger door in-flight, likely resulting in 

damage to airframe and systems and, under 

less favorable circumstances, loss of control 

of the aircraft. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 21, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 21, 2008. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on March 27, 2008 (73 FR 

16219). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

At least one incident has occurred where, 

immediately after take-off, the passenger door 

of a Dornier 328 completely opened. The 

flight crew reportedly had no cockpit 

indication or audible chime prior to this 

event. The aircraft returned to the departure 

airfield and made an uneventful emergency 

landing. Substantial damage to the door, 

handrails, door hinge arms and fuselage skin 

were found. 

The subsequent investigation could not 

find any deficiency in the design of the main 

cabin door locking mechanism. In addition, 

no technical failure could be determined that 

precipitated the event. The flight data 

recorder showed that the door was closed 

and locked before take-off and opened 

shortly afterward. Although final proof could 

not be obtained, the most likely way in 

which the door opened was that the door 

handle was inadvertently operated during the 

take-off run. 

In response to the incident, AvCraft (the 

TC (type certificate) holder at the time) 


rwilkins on PROD1PC63 with RULES
40956 Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations 

developed a placard set to warn the 

occupants against touching the door handle, 

as well as a structural modification of the 

passenger door hinge supports to make 

certain that the door does not separate from 

the aircraft when inadvertently opened 

during flight, allowing a safe descent and 

landing. 

Although the event described above did 

not prevent the flight crew from landing the 

aircraft safely, the condition of the aircraft 

immediately after the opening of the door has 

been determined to have been unsafe. [T]his 

Airworthiness Directive (AD) aims to prevent 

further incidents of inadvertent opening and 

possible detachment of a passenger door inflight, likely resulting in damage to airframe 

and systems and, under less favorable 

circumstances, loss of control of the aircraft. 

* * * * * 

Corrective actions include installing 

warning placards on the doors, and 

doing a modification that includes 

replacing the hinge supports and 

support struts of the passenger doors 

with new, improved hinge supports and 

support struts. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter provided information on an 

incident that occurred on a Dornier 

Model 228 airplane and asked for the 

procedure for reporting the incident to 

additional agencies so that appropriate 

action is taken. The applicability in the 

NPRM is for Dornier Model 328–100 

and –300 airplanes; therefore, the 

comment does not apply to this AD. The 

comment has been forwarded to the 

appropriate FAA office and will be 

addressed by that office accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

106 products of U.S. registry. We also 

estimate that it will take 38 work-hours 

per product to comply with the basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $11,961 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$1,590,106, or $15,001 per product. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2008–14–16 328 Support Services GmbH 

(Formerly AvCraft Aerospace GmbH 

formerly Fairchild Dornier GmbH, 

formerly Dornier Luftfahrt GmbH): 

Amendment 39–15611. Docket No. 

FAA–2008–0362; Directorate Identifier 

2007–NM–308–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 21, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 328 Support 

Services GmbH Dornier Model 328–100 

airplanes, having serial numbers (S/Ns) 3005 

through 3098, 3100, 3101, 3106, 3107, 3109, 

3110, 3112, 3113, 3115, 3117 and 3119; and 

Model 328–300 airplanes, having S/Ns 3102, 

3105, 3108, 3111, 3114, 3116, 3118, and 3120 

through 3224; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 11: Placards and Markings; 

and Code 52: Doors. 


rwilkins on PROD1PC63 with RULES
Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations 40957 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

At least one incident has occurred where, 

immediately after take-off, the passenger door 

of a Dornier 328 completely opened. The 

flight crew reportedly had no cockpit 

indication or audible chime prior to this 

event. The aircraft returned to the departure 

airfield and made an uneventful emergency 

landing. Substantial damage to the door, 

handrails, door hinge arms and fuselage skin 

were found. 

The subsequent investigation could not 

find any deficiency in the design of the main 

cabin door locking mechanism. In addition, 

no technical failure could be determined that 

precipitated the event. The flight data 

recorder showed that the door was closed 

and locked before take-off and opened 

shortly afterward. Although final proof could 

not be obtained, the most likely way in 

which the door opened was that the door 

handle was inadvertently operated during the 

take-off run. 

In response to the incident, AvCraft (the 

TC (type certificate) holder at the time) 

developed a placard set to warn the 

occupants against touching the door handle, 

as well as a structural modification of the 

passenger door hinge supports to make 

certain that the door does not separate from 

the aircraft when inadvertently opened 

during flight, allowing a safe descent and 

landing. 

Although the event described above did 

not prevent the flight crew from landing the 

aircraft safely, the condition of the aircraft 

immediately after the opening of the door has 

been determined to have been unsafe. [T]his 

Airworthiness Directive (AD) aims to prevent 

further incidents of inadvertent opening and 

possible detachment of a passenger door inflight, likely resulting in damage to airframe 

and systems and, under less favorable 

circumstances, loss of control of the aircraft. 

* * * * * 

Corrective actions include installing warning 

placards on the doors, and doing a 

modification that includes replacing the 

hinge supports and support struts of the 

passenger doors with new, improved hinge 

supports and support struts. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 30 days after the effective date 

of this AD, install warning placards on the 

inside of the passenger door and service 

doors, in accordance with the 

Accomplishment Instructions of Dornier 

Service Bulletin SB–328–11–454 (for Model 

328–100 airplanes) or SB–328J–11–209 (for 

Model 328–300 airplanes), both dated May 3, 

2004, as applicable. 

(2) Within 12 months after the effective 

date of this AD, modify the hinge supports 

and support struts of the passenger doors, in 

accordance with the Accomplishment 

Instructions of Dornier Service Bulletin SB–

328–52–460 (for Model 328–100 airplanes) or 

SB–328J–52–213, (for Model 328–300 

airplanes), both dated February 4, 2005, as 

applicable. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Send 

information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2007–0199, dated July 25, 2007 

(corrected July 26, 2007), and the service 

bulletins described in Table 1 of this AD, for 

related information. 

TABLE 1.—SERVICE INFORMATION

Dornier Service Bulletin Dated 

SB–328–11–454 .................................................................................................................................................................... May 3, 2004. 

SB–328–52–460 .................................................................................................................................................................... February 4, 2005. 

SB–328J–11–209 ................................................................................................................................................................... May 3, 2004. 

SB–328J–52–213 ................................................................................................................................................................... February 4, 2005. 

Material Incorporated by Reference 

(i) You must use the service information 

specified in Table 2 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE

Dornier Service Bulletin Dated 

SB–328–11–454 .................................................................................................................................................................... May 3, 2004. 

SB–328–52–460 .................................................................................................................................................................... February 4, 2005. 

SB–328J–11–209 ................................................................................................................................................................... May 3, 2004. 

SB–328J–52–213 ................................................................................................................................................................... February 4, 2005. 

(Only the title page of these documents 

contains the revision level and date of the 

documents.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact 328 Support Services GmbH, 

P.O. Box 1252, D–82231 Wessling, Federal 

Republic of Germany. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 


rwilkins on PROD1PC63 with RULES
40958 Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations 

Issued in Renton, Washington, on June 26, 

2008. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–15709 Filed 7–16–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0232; Directorate 

Identifier 2007–NM–309–AD; Amendment 

39–15612; AD 2008–14–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and A340–300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During fatigue tests (EF3) on the A340–600, 

multiple damage were found in the upper 

side shell structure at skin and frame (FR) 84 

& 85 interface, from stringer 6 to 15 LH/RH. 

This damage occurred between 58,341 and 

72,891 simulated Flight Cycles (FC). 

Due to the higher Design Service Goal and 

different design (e.g. skin thickness) for 

A330–200 and A340–300 aircraft series, the 

damage assessment concluded on [a] 

potential impact on these aircraft series. 

* * * * * 

The unsafe condition is loss of integrity 

of the upper shell structure of the 

fuselage. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

August 21, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 21, 2008. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building, Ground Floor, Room W12–

140, 1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on March 3, 2008 (73 FR 

11364). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During fatigue tests (EF3) on the A340–600, 

multiple damage were found in the upper 

side shell structure at skin and frame (FR) 84 

& 85 interface, from stringer 6 to 15 LH/RH. 

This damage occurred between 58,341 and 

72,891 simulated Flight Cycles (FC). 

Due to the higher Design Service Goal and 

different design (e.g. skin thickness) for 

A330–200 and A340–300 aircraft series, the 

damage assessment concluded on [a] 

potential impact on these aircraft series. 

In order to allow early detection of cracks 

which could avoid possible crack 

propagation and consequently to maintain 

the structural integrity of the upper side shell 

structure between FR84 and FR87, this 

Airworthiness Directive (AD) mandates an 

inspection program of this area [for cracking] 

using a high frequency eddy current (HFEC) 

method and a modification to improve the 

upper shell structure. 

This Revision 1 is issued to clarify that this 

AD is not applicable to aircraft A340–300 

series on which both AIRBUS modifications 

44205 and 45012 have been embodied in 

production. 

The unsafe condition is loss of integrity 

of the upper shell structure of the 

fuselage between FR84 and FR87. 

Corrective actions include contacting 

Airbus and repairing any crack. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Remove Reference to 

Modification 

Air Transport Association (ATA) on 

behalf of its member Northwest Airlines 

(NWA), requests that we remove the 

reference to Airbus Modification (Mod.) 

44205 from paragraph (c), 

‘‘Applicability,’’ of the NPRM. The 

commenters explain that Mod. 44205 

defines common structure for Section 

19. Mod. 45012, which is in paragraph 

(f)(1) of the NPRM, modifies the Section 

19 upper side shell on A330–200 series 

airplanes. 

We disagree. Cracks can develop on 

this area of Section 19 that affect basic 

airplanes fitted with the same features 

(i.e., post-Mod. 44205). For Model 

A340–300 series airplanes, Mod. 45012 

addresses the unsafe condition. 

Therefore, only Model A340–300 series 

airplanes on which both Mod. 44205 

and 45012 have been done in 

production are exempt. Analysis further 

to these findings established that 

cracking would also affect airplanes 

post-Mod. 45012 on Model A330–200 

series airplanes. The mandated action 

separates pre- or post-Mod. 45012, as 

specified in paragraphs (f)(1) and (f)(2) 

of this AD. We have made no change to 

the AD in this regard. 

Request To Exclude Certain Airplanes 

The same commenters request that we 

exclude from paragraph (f)(1) and Table 

1 of the NPRM airplanes that have Mod. 

52974 or 53223 embodied. The 

commenters explain that paragraph (c) 

excludes these airplanes, but paragraph 

(f)(1) and Table 1 do not exclude them. 

Without the exclusion, four more NWA 

airplanes are affected by the AD. 

We disagree. Paragraph (f)(1), which 

includes Table 1, refers to paragraph (c) 

where the two modifications are listed 

as exclusions. There is no need to 

exclude the airplanes again in paragraph 

(f)(1) or Table 1 of the AD. We have 

made no change to the AD in this 

regard. 

Request To Move ‘‘Before Further 

Flight’’ Requirement 

The same commenters request that we 

move the requirement to ‘‘Do all 

applicable corrective actions before 

further flight’’ from paragraph (f)(1) of 

the NPRM to the ‘‘Threshold’’ column of 

Table 1 of the NPRM. The commenters 

explain that moving this statement 

would make it clear that corrective 

action is required at the time of the 

mandated inspection thresholds and not 

before. 

We disagree. Paragraph (f)(1)(i) of this 

AD, which includes Table 1, gives 

thresholds for doing the HFEC 

inspection. Paragraph (f)(1)(ii) of this 

AD also gives a possible threshold for 

the HFEC inspection. The requirement 

is to do the applicable corrective actions 

before further flight. We have made no 

change to the AD in this regard. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 


rwilkins on PROD1PC63 with RULES