12072 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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://dms.dot.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 the 

NPRM, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) 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: 

2007–06–03 Airbus: Amendment 39–14984. 

Docket No. FAA–2007–26834; 

Directorate Identifier 2006–NM–235–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 19, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330 

airplanes, all certified models, certificated in 

any category, all serial numbers up to 755 

included. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

one Model A330 operator discovered that the 

line connection to the discharge head could 

not be properly secured during engine fire 

bottle replacement, due to a missing 

retaining-ring. Inspections revealed that all 

four discharge-heads line connectors, two per 

engine, were missing the retaining-ring. It 

was confirmed later that it was a quality 

issue. The function of the retaining-ring is to 

secure a tight connection between the fireextinguishing line and the discharge head. In 

absence of the retaining-ring, in case of 

activation of the fire extinguishing system, 

the pressure exerted by the agent on the pipe 

could compromise the tightness of the 

connection, leading to an incomplete 

discharge of the extinguishing agent in the 

fire zone. This situation if not corrected 

could lead, in the worst case, in combination 

with an engine fire, to a temporary 

uncontrolled engine fire which constitutes an 

unsafe condition. The MCAI requires a onetime detailed visual inspection for the 

presence of the retaining-ring on the 

discharge head assembly of engine fire 

extinguishing system, and repair if necessary. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. Within 900 flight hours from the 

effective date of this AD: On both engine 

pylons (left hand and right hand), for all four 

engine fire extinguisher bottles, two per 

engine pylon, perform a one-time detailed 

visual inspection for the presence of the 

retaining ring on the discharge head of the 

bottles and apply all applicable corrective 

actions, in accordance with instructions 

defined in Airbus Service Bulletin A330–

26A3037, dated July 26, 2006. Do all 

applicable corrective actions before further 

flight. Aircraft on which the four engine fire 

extinguishing bottles, 2 per engine pylon, 

have been removed and re-installed at the 

opportunity of hydrostatic test of engine fire 

extinguishing as per Airbus A330 

Maintenance Review Board Report (MRBR) 

task 26.21.00/04, are not concerned by this 

AD. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, Attn: Todd Thompson, 

Aerospace Engineer, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Before using any AMOC approved 

in accordance with § 39.19 on any airplane 

to which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(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. 

Material Incorporated by Reference 

(g) You must use Airbus Service Bulletin 

A330–26A3037, excluding Appendix 01, 

dated July 26, 2006, 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 Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

(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. 

Issued in Renton, Washington, on March 5, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4380 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26516; Directorate 

Identifier 2006–NM–173–AD; Amendment 

39–14983; AD 2007–06–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Airbus Model 

A318–100 and A319–100 series 

airplanes, Model A320–111 airplanes, 

and Model A320–200, A321–100, and 

A321–200 series airplanes. That AD 

currently requires repetitive inspections 

of the upper and lower attachments of 

the trimmable horizontal stabilizer 

actuator (THSA) to measure for proper 


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clearance and to detect cracks, damage, 

and metallic particles. The existing AD 

also requires corrective actions, if 

necessary, and reports of inspection 

findings. This new AD shortens the 

repetitive interval for inspecting the 

upper THSA attachment. This AD 

results from new test results on the 

secondary load path, which indicated 

the need to shorten the repetitive 

interval for inspecting the upper THSA 

attachment. We are issuing this AD to 

detect and correct failure of the THSA’s 

primary load path, which could result 

in latent (undetected) loading and 

eventual failure of the THSA’s 

secondary load path and consequent 

uncontrolled movement of the 

horizontal stabilizer and loss of control 

of the airplane. 

DATES: This AD becomes effective April 

19, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of Airbus Service Bulletin A320–27–

1164, Revision 04, including Appendix 

01, dated July 17, 2006, as of April 19, 

2007. 

On May 5, 2006 (71 FR 16203, March 

31, 2006), the Director of the Federal 

Register approved the incorporation by 

reference of Airbus Service Bulletin 

A320–27–1164, Revision 03, including 

Appendix 01, dated August 24, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–07–09, amendment 

39–14536 (71 FR 16203, March 31, 

2006). The existing AD applies to all 

Airbus Model A318–100 and A319–100 

series airplanes, Model A320–111 

airplanes, and Model A320–200, A321–

100, and A321–200 series airplanes. 

That NPRM was published in the 

Federal Register on December 8, 2006 

(71 FR 71103). That NPRM proposed to 

continue to require the existing actions 

(repetitive inspections of the upper and 

lower attachments of the trimmable 

horizontal stabilizer actuator (THSA) to 

measure for proper clearance and to 

detect cracks, damage, and metallic 

particles; corrective actions, if 

necessary; and reports of inspection 

findings). That NPRM proposed to 

shorten the repetitive interval for 

inspecting the upper THSA attachment. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request To Extend Repetitive Interval 

The NPRM proposed to reduce the 

existing repetitive interval for 

inspecting the upper attachment—from 

20 months to 10 months. Agreeing with 

the intent of the AD, Northwest Airlines 

nonetheless requests that we change this 

inspection interval to 11 months. The 

commenter reports that Northwest 

Airlines’ inspection of 139 affected 

airplanes during accomplishment of AD 

2006–07–09 has revealed no findings. 

Northwest Airlines is currently working 

with Airbus to better understand the 

reasons for the reduced inspection 

interval for the upper attachment. 

Northwest Airlines’ current L-check 

interval is 21.5 months. The commenter 

therefore feels that an inspection 

interval of 11 months for the upper 

attachment would allow Northwest 

Airlines to accomplish alternate 

inspections in a hangar, and yet fulfill 

the intent of the AD. The commenter 

explains that a hangar environment 

would allow the use of a more effective, 

specialized workforce, and reduce the 

impact of correcting any finding. 

We disagree with the request to 

extend the compliance time. The 

absence of positive findings alone does 

not justify an extension of the 

compliance time in this case. The 10- 

month inspection interval for the upper 

attachment is based on the results of 

Airbus’s tests of the endurance of the 

secondary load path under simulated 

loads. Northwest Airlines did not 

provide any data that would support the 

extension of the compliance time. We 

have not changed the final rule. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD, per inspection 

cycle. 

ESTIMATED COSTS

Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

1 ........................................................................................... $80 None $80 700 $56,000 

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 


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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 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14536 (71 

FR 16203, March 31, 2006) and by 

adding the following new airworthiness 

directive (AD): 

2007–06–02 Airbus: Amendment 39–14983. 

Docket No. FAA–2006–26516; 

Directorate Identifier 2006–NM–173–AD. 

Effective Date 

(a) This AD becomes effective April 19, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2006–07–09. 

Applicability 

(c) This AD applies to all Airbus Model 

A318, A319, A320, and A321 airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD results from new test results 

on the secondary load path, which indicated 

the need to shorten the repetitive interval for 

inspecting the upper attachment of the 

trimmable horizontal stabilizer actuator 

(THSA). We are issuing this AD to detect and 

correct failure of the THSA’s primary load 

path, which could result in latent 

(undetected) loading and eventual failure of 

the THSA’s secondary load path and 

consequent uncontrolled movement of the 

horizontal stabilizer and loss of control of 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. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Repetitive Inspections: Lower THSA 

Attachment 

(f) Within 20 months since first flight of the 

airplane, or within 600 flight hours after May 

5, 2006 (the effective date of AD 2006–07–

09), whichever occurs later: Do detailed 

inspections of the lower THSA attachments 

for proper clearances, and do related 

corrective actions as applicable, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

27–1164, Revision 03, including Appendix 

01, dated August 24, 2005; or Revision 04, 

including Appendix 01, dated July 17, 2006. 

After the effective date of this AD, only 

Revision 04 of the service bulletin may be 

used. Do corrective actions before further 

flight. Repeat the inspection thereafter at 

intervals not to exceed 20 months. 

Repetitive Inspections: Upper THSA 

Attachment 

(g) At the earlier of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: Do 

detailed inspections of the upper THSA 

attachment for cracks, damage, or metallic 

particles, and do related corrective actions as 

applicable, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1164, Revision 04, 

including Appendix 01, dated July 17, 2006, 

except as required by paragraph (h) of this 

AD. Do corrective actions before further 

flight. Repeat the inspections thereafter at 

intervals not to exceed 10 months. 

(1) At the latest of the times specified in 

paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of 

this AD. 

(i) Within 10 months since the first flight 

of the airplane. 

(ii) Within 10 months after the most recent 

inspection of the upper THSA attachment 

done in accordance with Airbus Service 

Bulletin A320–27–1164, Revision 02, 

including Appendix 01, dated March 30, 

2005; Revision 03, including Appendix 01, 

dated August 24, 2005; or Revision 04, 

including Appendix 01, dated July 17, 2006. 

(iii) Within 100 days after the effective date 

of this AD. 

(2) Within 20 months after the most recent 

inspection of the upper THSA attachment 

done in accordance with Airbus Service 

Bulletin A320–27–1164, Revision 02, 

including Appendix 01, dated March 30, 

2005; Revision 03, including Appendix 01, 

dated August 24, 2005; or Revision 04, 

including Appendix 01, dated July 17, 2006. 

Repair Exceptions 

(h) If any metallic particles are detected 

during any inspection required by paragraph 

(g) of this AD: Repair the damage before 

further flight in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the Direction Generale de 

l’Aviation Civile (DGAC) (or its delegated 

agent); or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Acceptable Prior Actions 

(i) Inspections of the lower THSA 

attachment done before May 5, 2006, in 

accordance with Airbus Alert Service 

Bulletin A320–27A1164, dated September 

10, 2004; or Airbus Service Bulletin A320–

27–1164, Revision 01, including Appendix 

01, dated December 17, 2004; are acceptable 

for compliance with the inspection 

requirements of paragraph (f) of this AD. 

(j) Actions done before the effective date of 

this AD in accordance with Airbus Service 

Bulletin A320–27–1164, Revision 02, 

including Appendix 01, dated March 30, 

2005; or Revision 03, including Appendix 01, 

dated August 24, 2005; are acceptable for 

compliance with the corresponding 

requirements of paragraphs (f) and (g) of this 

AD. 

Inspection Reports 

(k) At the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD, send a 

report of the positive findings of all 

inspections required by paragraphs (f) and (g) 

of this AD to Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. The 

report must include the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

landings and flight hours on the airplane. 

Using Appendix 01 of Airbus Service 

Bulletin A320–27–1164, Revision 02, dated 

March 30, 2005; Revision 03, dated August 

24, 2005; or Revision 04, dated July 17, 2006; 

is an acceptable method to comply with this 

paragraph. Under the provisions of the 

Paperwork Reduction Act (44 U.S.C. 3501 et 

seq.), the Office of Management and Budget 

(OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) For any inspection done before the 

effective date of this AD: Send the report 


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within 30 days after the effective date of this 

AD. 

(2) For any inspection done after the 

effective date of this AD: Send the report 

within 30 days after the inspection. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(m) EASA airworthiness directive 2006–

0223, dated July 21, 2006, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(n) You must use Airbus Service Bulletin 

A320–27–1164, Revision 03, including 

Appendix 01, dated August 24, 2005; or 

Airbus Service Bulletin A320–27–1164, 

Revision 04, including Appendix 01, dated 

July 17, 2006; as applicable; to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Airbus Service Bulletin A320–27–1164, 

Revision 04, including Appendix 01, dated 

July 17, 2006, in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On May 5, 2006 (71 FR 16203, March 

31, 2006), the Director of the Federal Register 

approved the incorporation by reference of 

Airbus Service Bulletin A320–27–1164, 

Revision 03, including Appendix 01, dated 

August 24, 2005. 

(3) Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. 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/ibr-locations.html. 

Issued in Renton, Washington, on March 2, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4382 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26231; Directorate 

Identifier 2006–CE–61–AD; Amendment 39–

14985; AD 2007–06–04] 

RIN 2120–AA64 

Airworthiness Directives; EADS 

SOCATA Model TBM 700 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) 

issued 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 two fatigue failures of flap 

carriage rollpins that occurred on inservice airplanes. We are issuing this 

AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective April 

19, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 19, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Albert J. Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4119; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

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 December 26, 2006 (71 FR 

77310). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states reports of 

two fatigue failures of flap carriage 

rollpins that occurred on in-service 

airplanes. The MCAI requires inspecting 

and applying torque values to the 

rollpins nuts. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Comment Issue No. 1: Use Consistent 

Language 

Raymond S. Benischeck comments on 

this AD due to the fact there is 

inconsistent language regarding the 

identification of the part in question. 

The commenter states: 

In portions of the NPRM we are told to 

inspect for a fracture of the flap carriage 

‘‘ROLLPINS.’’ Elsewhere, the correct 

terminology ‘‘ROLLER PINS’’ is used. The 

correct terminology should be used 

throughout the document. 

The terminology used within the 

Discussion and Reason sections was 

copied directly from the associated 

MCAI. We are currently trying to use the 

language provided to us by the foreign 

airworthiness authority whenever 

possible. For consistency, we will 

change the phrase ‘‘roller pin’’ to 

‘‘rollpin’’ in the final rule AD action to 

coincide with the MCAI. 

We are changing the final rule AD 

action based on this comment. 

Comment Issue No. 2: Clarify Paragraph 

(e)(1) of the Proposed AD 

Raymond S. Benischeck comments 

that clarification may be necessary in 

paragraph (e)(1) of the proposed AD in 

which instructions are given to check 

for correct torque of the roller pin. 

Although applying correct torque 

should reveal any discrepancies in this 

roller pin, the actual inspection is for 

the purposes of detecting broken 

rollpins. 


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