21090 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations 

Applicability 

(c) This AD applies to all EMBRAER Model 

ERJ 170–100 LR, –100 STD, –100 SE, –100 

SU, –200 LR, –200 STD, and –200 SU 

airplanes; and ERJ 190–100 STD, –100 LR, 

and –100 IGW airplanes; certificated in any 

category. 

Unsafe Condition 

(d) This AD results from a report indicating 

that the aft cargo door of a Model ERJ 190 

airplane opened in flight just after departure, 

and from a report indicating that a Model ERJ 

170 airplane dispatched with an unsecured 

forward cargo door. The Federal Aviation 

Administration is issuing this AD to prevent 

a cargo door from opening during flight, 

which could lead to structural failure or loss 

of control. 

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. 

Preflight Verifications of Correct Door 

Closure 

(f) As of 24 hours after the effective date 

of this AD: Before each flight after closing the 

cargo doors, verify that the forward and aft 

cargo doors are closed flush with the fuselage 

skin, and that all 4 latched and locked 

indicators at the bottom of each door are 

green. Persons qualified to do this 

verification are mechanics and flightcrew 

members. If it cannot be verified that both 

doors are closed flush with the fuselage skin, 

and that all 4 latched and locked indicators 

at the bottom of each door are green, repair 

before further flight. Repeat the verification 

before every flight until accomplishment of 

the actions required by paragraph (g) of this 

AD. 

Inspection for Interference and Damage 

(g) Within 10 days after the effective date 

of this AD, do the actions specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD, 

in accordance with the Accomplishment 

Instructions of EMBRAER Alert Service 

Bulletin 170–52–A036 (for Model ERJ 170 

airplanes) or 190–52–A018 (for Model ERJ 

190 airplanes), both dated March 12, 2007, as 

applicable. 

(1) Remove the roller fitting cover plate on 

the forward and aft cargo door frames. 

(2) Perform a detailed inspection of the 

forward and aft cargo doors to detect signs of 

interference between the lock handle and the 

aft edge liner assembly. Then rework the aft 

edge liner assembly at the applicable time 

specified in paragraph (g)(2)(i) or (g)(2)(ii) of 

this AD. 

(i) If any sign of interference is detected: 

Rework the assembly before further flight. 

(ii) If no sign of interference is detected: 

Rework the assembly within 150 flight cycles 

after the inspection. 

(3) Perform a detailed inspection for signs 

of damage of the lateral roller fitting on the 

forward and aft cargo door frames at the 

fuselage. If any damage is found, replace the 

lateral roller fitting before further flight with 

a new roller fitting having the same part 

number, in accordance with the applicable 

service bulletin. 

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.’’

Note 2: EMBRAER Alert Service Bulletins 

170–52–A036 and 190–52–A018 refer to 

EMBRAER Service Bulletins 170–50–0006 

and 190–50–0006, respectively, as additional 

sources of service information for the rework 

and roller fitting cover plate removal. Service 

Bulletins 170–50–0006 and 190–50–0006 are 

currently at Revision 01, dated March 13, 

2007. 

Repetitive Inspection for Damage 

(h) Repeat the inspection specified in 

paragraph (g)(3) of this AD at intervals not to 

exceed 150 flight cycles. 

Report 

(i) At the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD: Send 

EMBRAER a report of any signs of 

interference or damage found during each 

inspection required by paragraphs (g)(2), 

(g)(3), and (h) of this AD. 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. Send the 

report to EMBRAER, EFTC, AOG Structure 

Team; structure@embraer.com.br; fax +55 12 

3927 6600, extension 0484. 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 after the 

effective date of this AD: Within 10 days after 

the inspection. 

(2) For any inspection done before the 

effective date of this AD: Within 10 days after 

the effective date of this AD. 

Parts Installation 

(j) As of the effective date of this AD: No 

person may install a roller fitting cover plate 

on the forward and aft cargo door frames on 

any airplane. 

Alternative Methods of Compliance 

(AMOCs) 

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

ANM–116, Transport Airplane Directorate, 

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. 

Related Information 

(l) Brazilian airworthiness directives 2007–

03–01 and 2007–03–02, both effective March 

16, 2007, also address the subject of this AD. 

Material Incorporated by Reference 

(m) You must use EMBRAER Alert Service 

Bulletin 170–52–A036, dated March 12, 

2007; or EMBRAER Alert Service Bulletin 

190–52–A018, dated March 12, 2007; as 

applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of these documents in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. To 

get copies of the service information, contact 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), P.O. Box 343—CEP 12.225, Sao 

Jose dos Campos—SP, Brazil. 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 April 17, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7841 Filed 4–27–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25581 Directorate 

Identifier 2006–CE–041–AD; Amendment 

39–15039; AD 2007–09–07] 

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: 

* * * a Nose Landing Gear (NLG) hinge 

pin rupture that causes an uncommanded 

NLG retraction. 

Investigations identified the unsafe 

condition resulting from an incomplete 

thermal treatment done on three hinge pin 


pwalker on PROD1PC71 with RULES
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations 21091 

batches lowering their mechanical properties 

with a high risk of deformation under service 

loads. 

EADS SOCATA notes that an NLG hinge 

pin rupture could cause an 

uncommanded NLG retraction during 

landing. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective June 

4, 2007. 

On June 4, 2007 the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

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 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 supplemental 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 February 21, 2007 

(72 FR 7838). That NPRM proposed to 

correct an unsafe condition for the 

specified products. The MCAI advises of 

* * * a Nose Landing Gear (NLG) hinge 

pin rupture that causes an uncommanded 

NLG retraction. 

Investigations identified the unsafe 

condition resulting from an incomplete 

thermal treatment done on three hinge pin 

batches lowering their mechanical properties 

with a high risk of deformation under service 

loads. 

EADS SOCATA notes that an NLG hinge 

pin rupture could cause an 

uncommanded NLG retraction during 

landing. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Comment Issue No. 1: Number of 

Affected Products 

EADS SOCATA writes that TBM 

Aircraft Mandatory Alert Service 

Bulletin SB 70–147, Amendment 1, 

dated September 2006, affects 86 nose 

landing gear (NLG) (in the worst case 86 

products). Further, that among these 86 

NLG, only 47 NLG are equipped with 

defective pins. 

The FAA agrees that not all aircraft 

contain the affected NLG part. However, 

to appropriately identify the product 

with the affected nose landing gear part 

serial number, the AD requires to first 

identify the concerned NLG, then to 

detect the defective hinge pins installed 

on the product, and then replace the 

affected parts. The check of the NLG 

part serial number for applicability is 

necessary on all products. Therefore, we 

are not changing the AD based on this 

comment. 

Comment Issue No. 2: Cost of 

Compliance 

EADS SOCATA notes that the 

proposed AD specifies that any required 

parts would cost about $1,025 for each 

product and that it would take about 2 

work-hours per product to comply with 

basic requirements of this proposed AD. 

EADS SOCATA specifies that the 

identification of the batch number is 

immediate for products with correct 

pins. For any product with defective 

pins, all the costs, work-hours and 

required parts, associated with TBM 

Aircraft Mandatory Alert Service 

Bulletin SB 70–147, Amendment 1, 

dated September 2006, will be covered 

under warranty if the defective pins are 

returned to EADS SOCATA. 

We have noted EADS SOCATA 

comments and have revised the costs of 

compliance to reflect only the labor to 

identify the NLG part serial number. 

Our standard warranty language will 

reflect EADS SOCATA’s warranty 

program. 

Comment Issue No. 3: Unsafe Condition 

Description 

EADS SOCATA comments that the 

proposed AD describes the unsafe 

condition associated with TBM Aircraft 

Mandatory Alert Service Bulletin SB 

70–147, Amendment 1, dated 

September 2006, as an NLG hinge pin 

rupture that causes an uncommanded 

NLG retraction. Further, EADS SOCATA 

estimates that a NLG hinge pin rupture 

could lead to a nose landing gear 

collapse in the case of a three-point 

landing. 

The FAA notes that the unsafe 

condition language was copied directly 

from the Reason section of the 

associated MCAI. However, to clarify 

the unsafe condition we will change the 

AD to add that a NLG hinge pin rupture 

could cause an uncommanded NLG 

retraction during landing. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

256 products of U.S. registry. We also 

estimate that it will take about 0.5 workhours per product to comply with basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Based on these figures, we estimate 

the cost of this AD to the U.S. operators 

to be $10,240 or $40 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 


pwalker on PROD1PC71 with RULES
21092 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations 

affected parties, some parties may incur 

costs higher than estimated here. 

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 

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: 

2007–09–07 EADS SOCATA: Amendment 

39–15039; Docket No. FAA–2006–25581; 

Directorate Identifier 2006–CE–041–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 4, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Model TBM 700 

airplanes fitted with nose landing gear (NLG) 

part number (P/N) 21130–001–02 with serial 

numbers (S/N) B155 through B173 and S/N 

EUR 174 through EUR 240, that are 

certificated in any U.S. category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) describes 

the unsafe condition as follows: 

* * * a Nose Landing Gear (NLG) hinge 

pin rupture that causes an uncommanded 

NLG retraction. 

Investigations identified the unsafe 

condition resulting from an incomplete 

thermal treatment done on three hinge pin 

batches lowering their mechanical properties 

with a high risk of deformation under service 

loads. 

EADS SOCATA notes that an NLG hinge pin 

rupture could cause an uncommanded NLG 

retraction during landing. 

Actions and Compliance 

(f) Within 30 days after June 4, 2007 (the 

effective date of this AD), unless already 

done, do the following: 

(1) Identify the NLG hinge pin batch 

number as instructed in paragraph B of the 

accomplishment instructions of EADS 

SOCATA TBM Aircraft Mandatory Alert 

Service Bulletin SB 70–147, Amendment 1, 

dated September 2006. 

(i) For airplanes with the correct pin batch 

numbers, no further action is required. 

Return the airplane to service as instructed 

in EADS SOCATA TBM Aircraft Mandatory 

Alert Service Bulletin SB 70–147, 

Amendment 1, dated September 2006. 

(ii) For airplanes with pins from the 

defective pin batch numbers or for which the 

batch number cannot be read, do all the 

actions as instructed in paragraphs B 5), C, 

and D of the accomplishment instructions of 

EADS SOCATA TBM Aircraft Mandatory 

Alert Service Bulletin SB 70–147, 

Amendment 1, dated September 2006. 

(2) As of 30 days after June 4, 2007 (the 

effective date of this AD), do not install on 

any EADS SOCATA Model TBM 700 airplane 

an NLG actuator hinge pin coming from the 

three defective batches identified as EUR BC 

21344–000–01, EUR BD 21344–000–01, and 

EUR BF 21344–000–01 on NLG part number 

21130–001–02. 

FAA AD Differences 

Note: This AD differs from the MCAI 

and/or service information as follows: The 

service bulletin and MCAI require interim 

operational instructions until the corrective 

actions are done. This AD requires the 

corrective action at the same time as the pin 

batch number check. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: 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., has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(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 

(44 U.S.C. 3501 et. seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) This AD is related to European Aviation 

Safety Agency Emergency AD No. 2006–

0271–E, Issue date: September 4, 2006, which 

references EADS SOCATA TBM Aircraft 

Mandatory Alert Service Bulletin SB 70–147, 

Amendment 1, dated September 2006. 

Material Incorporated by Reference 

(i) You must use EADS SOCATA TBM 

Aircraft Mandatory Alert Service Bulletin SB 

70–147, Amendment 1, dated September 

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 


pwalker on PROD1PC71 with RULES
Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations 21093 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact EADS SOCATA, Direction 

des Services, 65921 Tarbes Cedex 9, France; 

telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 

62.41.76.54; or SOCATA Aircraft, INC., North 

Perry Airport, 7501 Airport Road, Pembroke 

Pines, Florida 33023; telephone: (954) 893–

1400; fax: (954) 964–4141. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; 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 Kansas City, Missouri, on April 

20, 2007. 

Charles L. Smalley, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–8003 Filed 4–27–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27208 Directorate 

Identifier 2007–CE–010–AD; Amendment 

39–15040; AD 2007–09–08] 

RIN 2120–AA64 

Airworthiness Directives; Vulcanair 

S.p.A. Model P68 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) 

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: 

The backrest recline of pilot and copilot 

seats requires the removal of a ‘‘quick release 

pin’’ not correctly indicated in the AFM and 

not ready detectable by the passengers. 

Moreover the operation of removal the device 

is difficult. This cause difficulty or disables 

the access to the escapes of the cabin in case 

of emergency evacuation. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

4, 2007. 

On June 4, 2007 the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

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: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4145; 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 March 9, 2007 (72 FR 

10620). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

The backrest recline of pilot and copilot 

seats requires the removal of a ‘‘quick release 

pin’’ not correctly indicated in the AFM and 

not ready detectable by the passengers. 

Moreover the operation of removal the device 

is difficult. This cause difficulty or disables 

the access to the escapes of the cabin in case 

of emergency evacuation. 

Carry out the operational cheks/inspection/ 

modification: 

—Kit SB 128/A–1 applicable to aircraft 

model P68C. Serial numbers (S/N) 429, 434 

and 435 are excluded; 

—Kit SB 128/A–2 applicable only to P68C 

aircraft with S/N 429, 434 and 435; 

—Kit SB 128/B applicable to aircraft model 

P68 Observer 2; 

—Kit SB 128/C applicable to aircraft model 

P68TC Observer; called for by the 

referenced Service Bulletin, in accordance 

with the procedures in there specified, 

within the terms set forth under 

‘‘COMPLIANCE’’ of this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data 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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

15 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 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 

$2,400 or $160 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 


pwalker on PROD1PC71 with RULES