This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

17879 

Vol. 75, No. 67 

Thursday, April 8, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0380; Directorate 

Identifier 2009–NM–009–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Cessna 

Aircraft Company Model 750 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Model 

750 airplanes. The existing AD currently 

requires inspecting the inboard-hinge 

brackets of the left and right elevators 

for cracking and doing related 

investigative and corrective actions if 

necessary. For certain airplanes, this 

proposed AD would require inspecting 

for cracks and corrosion of the bracket 

of the inboard horizontal stabilizer and 

measuring the lug thickness of the 

horizontal stabilizer hinges; doing 

corrective actions if necessary; 

modifying the left and right elevators 

and left and right horizontal stabilizer. 

For all airplanes, this proposed AD 

would require replacing the existing 

elevator assemblies with new elevator 

assemblies, which would terminate the 

requirements of the existing AD. This 

proposed AD would also revise the 

applicability to remove certain 

airplanes. This proposed AD results 

from a report of cracking and corrosion 

found on the elevator inboard-hinge 

brackets and the horizontal stabilizer 

hinges. We are issuing this AD to 

prevent such cracking and corrosion of 

the elevator inboard-hinge brackets and 

the horizontal stabilizer hinges, which 

could result in structural failure of the 

elevators and consequent loss of control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 24, 2010. 

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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Cessna 

Aircraft Co., P.O. Box 7706, Wichita, 

Kansas 67277; telephone 316–517–6215; 

fax 316–517–5802; e-mail 

citationpubs@cessna.textron.com; 

Internet https:// 

www.cessnasupport.com/newlogin.html. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: T.N. 

Baktha, Aerospace Engineer, Airframe 

Branch, ACE–118W, FAA, Wichita 

Aircraft Certification Office, 1801 

Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; 

telephone (316) 946–4155; fax (316) 

946–4107. 

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–2010–0380; Directorate Identifier 

2009–NM–009–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 

On October 26, 2006, we issued AD 

2006–23–05, Amendment 39–14817 (71 

FR 65047, November 7, 2006), for all 

The Cessna Aircraft Company Model 

750 airplanes. That AD requires 

inspecting the inboard-hinge brackets of 

the left and right elevators for cracking, 

and doing related investigative and 

corrective actions if necessary. That AD 

resulted from a report of cracking found 

on the elevator inboard-hinge brackets. 

We issued that AD to detect and correct 

cracking of the elevator inboard-hinge 

brackets, which could result in 

structural failure of the elevators and 

consequent loss of control of the 

airplane. 

Actions Since Existing AD Was Issued 

The preamble to AD 2006–23–05 

explains that we considered the 

requirements ‘‘interim action’’ and were 

considering further rulemaking if a final 

action is identified. We now have 

determined that further rulemaking is 

indeed necessary, and this proposed AD 

follows from that determination. 

Relevant Service Information 

We have reviewed Cessna Service 

Bulletin SB750–27–62, Revision 3, 

dated August 21, 2009, including 

Service Bulletin Supplemental Data, 

Revision D, dated September 18, 2009. 

That service bulletin describes 

procedures for the following: 


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17880 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 

• For certain airplanes, doing an eddy 

current inspection for cracks of the 

bracket of the inboard horizontal 

stabilizer; and corrective action, if 

necessary, which is replacing any 

cracked bracket of the inboard 

horizontal stabilizer with a serviceable 

bracket. 

• For certain airplanes, measuring the 

lug thickness of the horizontal stabilizer 

hinges; and corrective action, if 

necessary, which is replacing the 

bearing plate with a serviceable bearing 

plate if the lug thickness is not within 

the acceptable tolerance range. 

• For certain airplanes, modifying the 

left and right horizontal stabilizer, and 

adding the modification part number of 

the horizontal stabilizer to the 

modification section of the MS27253–1 

identification plate. 

• For all airplanes, replacing the left 

and right elevator assemblies with new 

elevator assemblies. 

Accomplishment of the applicable 

actions specified in Cessna Service 

Bulletin SB750–27–62, Revision 3, 

dated August 21, 2009, eliminates the 

need for the actions required by AD 

2006–23–05. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2006– 

23–05 and would retain the 

requirements of the existing AD. This 

proposed AD removes certain airplanes 

from the applicability of the existing 

AD. Cessna Model 750 airplanes with 

serial number 750–306 and subsequent 

are no longer subject to the 

requirements of this AD as Cessna has 

incorporated the applicable 

requirements in production. This 

proposed AD would also require 

accomplishing the actions specified in 

the ‘‘Relevant Service Information’’ 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Service Bulletin.’’ 

Differences Between the Proposed AD 

and Service Bulletin 

Cessna Service Bulletin SB750–27–62, 

Revision 3, dated August 21, 2009, 

specifies to do eddy current inspection 

for cracks of the bracket of the inboard 

horizontal stabilizer and replace any 

cracked brackets. This proposed AD 

would also require an inspection for 

corrosion and replacement of any 

corroded brackets. 

Change to Existing AD 

This proposed AD would retain the 

requirements of AD 2006–23–05. Since 

AD 2006–23–05 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2006–23–05 

Corresponding 

requirement in this 

proposed AD 

paragraph (d) paragraph (e) 

paragraph (e) paragraph (f) 

paragraph (f) paragraph (g) 

paragraph (g) paragraph (h) 

paragraph (h) paragraph (i) 

paragraph (i) paragraph (j) 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection (required by AD 

2006–23–05).

2 .................. $85 $0 ...................................... $170 ............ 253 $43,010. 

Modification and Replacement (new proposed actions).Up to 200 .... 85 The manufacturer states 

that it will supply parts 

to the operators at no 

cost.

Up to 

$17,000.

253 Up to 4,301,000. 

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 

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); 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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 


sroberts on DSKD5P82C1PROD with PROPOSALS
Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 17881 

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 

removing Amendment 39–14817 (71 FR 

65047, November 7, 2006) and adding 

the following new AD: 

The Cessna Aircraft Company: Docket No. 

FAA–2010–0380; Directorate Identifier 

2009–NM–009–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by May 24, 2010. 

Affected ADs 

(b) This AD supersedes AD 2006–23–05, 

Amendment 39–14817. 

Applicability 

(c) This AD applies to The Cessna Aircraft 

Company Model 750 airplanes, certificated in 

any category, as identified in Cessna Service 

Bulletin SB750–27–62, Revision 3, dated 

August 21, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Unsafe Condition 

(e) This AD results from a report of 

cracking and corrosion found on the elevator 

inboard-hinge brackets and the horizontal 

stabilizer hinges. The Federal Aviation 

Administration is issuing this AD to prevent 

cracking and corrosion of the elevator 

inboard-hinge brackets and the horizontal 

stabilizer hinges, which could result in 

structural failure of the elevators and 

consequent loss of control of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

RESTATEMENT OF REQUIREMENTS OF 

AD 2006–23–05, WITH NO CHANGES: 

Inspection 

(g) After the airplane accumulates 2,500 

total flight hours: Perform a general visual 

inspection for cracking of the inboard-hinge 

brackets of the left and right elevators in 

accordance with the Accomplishment 

Instructions of Cessna Alert Service Letter 

ASL750–27–21, dated October 13, 2006. Do 

the inspection before the airplane 

accumulates 3,000 total flight hours, or 

within 10 flight hours after November 22, 

2006 (the effective date of AD 2006–23–05), 

whichever is later. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to enhance visual access to 

all exposed surfaces in the inspection area. 

This level of inspection is made under 

normally available lighting conditions such 

as daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

Related Investigative and Corrective Actions 

(h) If any crack is found during the 

inspection required by paragraph (g) of this 

AD: Before further flight, perform an eddy 

current inspection of the inboard-hinge 

brackets to determine the crack length, in 

accordance with the Accomplishment 

Instructions of Cessna Alert Service Letter 

ASL750–27–21, dated October 13, 2006; and 

do the actions specified in paragraph (h)(1) 

or (h)(2) of this AD, as applicable, at the time 

specified. All corrective actions must be done 

using a method approved by the Manager, 

Wichita Aircraft Certification Office (ACO), 

FAA. For a replacement method to be 

approved by the Manager, Wichita ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

(1) If the crack is 0.30 inch or more: 

Replace the bracket before further flight. 

(2) If the crack is less than 0.30 inch: 

Continued flight for a maximum of 10 flight 

hours for repositioning of the airplane and 

replacement of the bracket is allowed, within 

the restricted flight envelope included in the 

attachment to Cessna Alert Service Letter 

ASL750–27–21, dated October 13, 2006, 

titled ‘‘Flight Restrictions.’’ 

Special Flight Permits 

(i) Special flight permits, as described in 

Section 39.23 of the Federal Aviation 

Regulations (14 CFR 39.23), are allowed with 

the limitations required by paragraph (h)(2) 

of this AD. 

No Reporting or Return of Parts to 

Manufacturer 

(j) Cessna Alert Service Letter ASL750–27– 

21, dated October 13, 2006, specifies 

submitting a sheet related to inspection 

results to the manufacturer; this AD does not 

include that requirement. The service letter 

also specifies sending the elevator assembly 

to the manufacturer for replacement of the 

inboard-hinge bracket if a crack is found that 

is 0.30 inch or more; however, this AD 

requires corrective actions be done using a 

method approved by us. 

NEW REQUIREMENTS OF THIS AD: 

(k) Within 60 months after the effective 

date of this AD, do the applicable actions 

required by paragraphs (k)(1), (k)(2), (k)(3), 

and (k)(4) of this AD, in accordance with the 

Accomplishment Instructions of Cessna 

Service Bulletin SB750–27–62, Revision 3, 

dated August 21, 2009. Accomplishing the 

actions required by paragraph (k) of this AD 

terminates the requirements of paragraphs (g) 

through (j) of this AD. 

(1) For all airplanes except those having 

S/Ns 288 through 305 inclusive: Do an eddy 

current inspection for cracks and corrosion of 

the bracket of the inboard horizontal 

stabilizer. Before further flight, replace any 

cracked or corroded bracket of the inboard 

horizontal stabilizer with a serviceable 

bracket. 

(2) For all airplanes except those having 

S/Ns 288 through 305 inclusive: Measure the 

lug thickness of the horizontal stabilizer 

hinges. If the lug thickness is not within the 

acceptable tolerance range, as identified in 

Cessna Service Bulletin SB750–27–62, 

Revision 3, dated August 21, 2009, before 

further flight, replace the bearing plate with 

a serviceable bearing plate. 

(3) For all airplanes except those having 

S/Ns 288 through 305 inclusive: Modify the 

left and right horizontal stabilizer; and add 

the modification part number of the 

horizontal stabilizer to the modification 

section of the MS27253–1 identification 

plate. 

(4) For all airplanes: Replace the existing 

elevator assemblies with new elevator 

assemblies having part numbers 6734000–17 

(for the left side) and 6734000–18 (for the 

right side). 

Credit for Actions Done Using the Previous 

Service Information 

(l) Actions accomplished before the 

effective date of this AD in accordance with 

the service bulletins identified in Table 1 of 

this AD are considered acceptable for 

compliance with the corresponding 

requirements of paragraph (k) of this AD. 

TABLE 1—CREDIT FOR PREVIOUS SERVICE BULLETINS

Service Bulletin Revision level Date 

Cessna Service Bulletin SB750–27–62 ......................................................................................... Original ........................ October 13, 2008. 

Cessna Service Bulletin SB750–27–62 ......................................................................................... 1 .................................. October 22, 2008. 

Cessna Service Bulletin SB750–27–62 ......................................................................................... 2 .................................. December 17, 2008. 


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17882 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Wichita 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. Send information to ATTN: T.N. 

Baktha, Aerospace Engineer, Airframe 

Branch, ACE–118W, FAA, Wichita ACO, 

1801 Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; telephone 

(316) 946–4155; fax (316) 946–4107. 

(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 principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Issued in Renton, Washington, on April 1, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7943 Filed 4–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0379; Directorate 

Identifier 2009–NM–210–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–300, –400, and 

–500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Model 

737–300, –400, and –500 series 

airplanes. The existing AD currently 

requires inspecting to determine if 

certain carriage spindles are installed, 

repetitive inspections for corrosion and 

indications of corrosion on affected 

carriage spindles, and if necessary, 

related investigative and corrective 

actions. The existing AD also provides 

an optional terminating action. This 

proposed AD would mandate the 

optional terminating action, which 

would eliminate the need for the 

repetitive inspections. The proposed AD 

results from reports of corrosion found 

on carriage spindles that are located on 

the outboard trailing edge flaps. We are 

proposing this AD to detect and correct 

corrosion of the carriage spindle, which 

could result in fracture. Fracture of both 

the inboard and outboard carriage 

spindles, in the forward ends through 

the large diameters, on a flap, could 

adversely affect the airplane’s continued 

safe flight and landing. 

DATES: We must receive comments on 

this proposed AD by May 24, 2010. 

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 20590, 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, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; 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, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590. 

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–2010–0379; Directorate Identifier 

2009–NM–210–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 

On October 26, 2009, we issued AD 

2009–23–10, Amendment 39–16084 (74 

FR 57564, November 9, 2009), for all 

Model 737–300, –400, and –500 series 

airplanes. That AD requires inspecting 

to determine if certain carriage spindles 

are installed, repetitive inspections for 

corrosion and indications of corrosion 

on affected carriage spindles, and if 

necessary, related investigative and 

corrective actions. That AD also 

provides an optional terminating action. 

That AD resulted from reports of 

corrosion found on carriage spindles 

that are located on the outboard trailing 

edge flaps. We issued that AD to detect 

and correct corrosion of the carriage 

spindle, which could result in fracture. 

Fracture of both the inboard and 

outboard carriage spindles, in the 

forward ends through the large 

diameters, on a flap, could adversely 

affect the airplane’s continued safe 

flight and landing. 

Actions Since Existing AD Was Issued 

The preamble to AD 2009–23–10 

explains that we consider the 

requirements ‘‘interim action’’ and were 

considering further rulemaking. We now 

have determined that further 

rulemaking is indeed necessary, and 

this proposed AD follows from that 

determination. 

Boeing Commercial Airplanes has 

received an Organization Designation 

Authorization (ODA), which replaces 

their previous designation as a 

Delegation Option Authorization (DOA) 

holder. We have revised paragraph (l)(3) 

of this AD to delegate the authority to 

approve an alternative method of 


sroberts on DSKD5P82C1PROD with PROPOSALS