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FEDERAL REGISTER

Tuesday, D ecem ber 4, 1956

CODIFICATION GUIDE Con.
Title 33

PaS

Chapter I:
Part 124.__________________________

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Title 43
Chapter I :
Appendix Public land orders :
909 revoked in part by P L O
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Title 47
Chapter I:
Part 3 proposed --------------------Part 21______________________

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Title 50
Chapter I :
Part 17__________ ___________

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Airworthiness Directives issued prior to June 17, 1950, were published in A p
pendix A to Part 1 of the Civil A ir R egu lations 15 P, R. 3872-3926. This part supersedes Appendix A to P a rt 1, and includes all Airworthiness Directives is sued subsequent to the issuance of such appendix, so that all Airworthiness D i rectives issued by the Adm inistrator will be codified in one part for the convenient reference of the users thereof.
Since the substance of the Airw orthi ness Directives contained in this part have been published in Appendix A to Part 1, or by individual notice to opera tors of aircraft; and since compliance with the provisions of such directives cannot, in the interest of safety, be sus pended to permit norm al rule-m aking procedures in accordance with section 4
of the Administrative Procedure Act, the following regulations are adopted to be come effective on publication in the F ed eral R egister .
Section 1.2-1 and Appendix A A ir worthiness Directives of Chapter I of-this title, as published in 15 F. R. 3872-3926, June 17, 1950; amended 15 F. R. 86238627, December 6, 1950, are hereby re scinded and the following P a rt 507 is adopted to read as follows:
Subpart A Genera
Sec.
507.1 Basis and purpose.
507.2 Definitions.
507.3

Criteria fo r
determ inin g com pliance
dates.
Subpart B Airworthiness Directive
507.10 General.
Authority : 507.1 to 507.3 issued under sec. 205, 52 Stat. 984, as amended; 49 U. S. C.
425. Interpret or apply sec. 601, 603, 52 Stat.
1007,1009; 49 U. S. C. 551, 553.
SUBPART A GENERAL

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B. Replacement required. Jig fixtures, Douglas Parts A652-5110506-1-1F2 and A65251105061F2 or equivalent, must be used to accomplish the replacement of the following attach angles anddoublers.
1. Defective angles. In case defective an gles are found, they must be replaced by 507.3 Criteria for determining com angles extruded 99 or the heavier type angles pliance dates.
The following criteria as outlined in Douglas Service Bulletin No.
w ill be used by the Administrator in de 146, before allowing further operation. In termining the compliance date a product case defective angles are found and they are identified as being angles extruded 99, they must be modified to comply with the A ir worthiness Directives in Subpart B of must be replaced by the heavier type angles as outlined in Douglas Service Bulletin No.
this part:
146 before allowing further operation.
a W h en an unsafe condition is dis 2. Doublers. In case cracked doublers are covered in a product, which renders the found at any of the specified inspections, aircraft unairworthy, the corrective ac they must be replaced. All lower surface tion specified in the Airworthiness D irec outer panel wing attach angle doublers Part Nos. 570602-206, -207, -208, and -209 must tive must be taken immediately.
b W h en an unsafe condition is dis be replaced at or before 16,000 hours total covered in a product, which m ay at some doubler time. After October 15, 1944, no future date render the aircraft un air aircraft will be permitted to continue in op eration having 16,000 hours total doubler worthy, a compliance date in the future time except as covered under Section C below.
will be prescribed in the Airworthiness Douglas Service Bulletin No. 220 dated Directive.
March 11, 1944, contains information on ac 1
In determining the complianceceptable methods o f accomplishing this re date under p aragraph b , the Adm inis work. After replacement of the doubler as trator will take into account the nature described in the paragraph above, it will be and amount of work involved, the avail satisfactory to add, the auxiliary gussets and shims, as shown on Douglas Drawing 570602, ability of parts, recommendations of the Change DLL.
m anufacturer and operators, and the e f 3. Refer to A. D. Note 52-22-3.
fectiveness of operating restrictions C. Opter wing heavy doubler installation.
which m ay mitigate the condition.
When the numbers 570602-206 and -207
doublers have been replaced with 0.072 ma SUBPART B AIRWORTHINESS DIRECTIVES
terial instead of 0.064 material and the 507.10 General. The Airworthiness 570602-208 and -209 doublers have been re Directives listed in this subpart specify placed with 0.064 material instead of 0.051
the products for which an unsafe condi material as recommended in Douglas Service tion has been found by the Adm inistra Bulletin DC-3 No. 220, they need not be re tor, and the conditions, limitations, or placed at 16,000 hours provided the following are accomplished:
inspections, if any, under which the 1. Complete inspection as required by A-2
product may continue to be operated: : above is conducted at 16,000 hours and no a
Summary of airworthiness direc cracks are found.
tives.
2. Complete inspection as required by A
39-24-1 Douglas Was Service Note 1 of above is conducted at intervals not to ex AD-618-3 and Service Note 1 of ADceed 2,000 hours after the 16,000-hour in spection has been completed.
669-3
3. Canceled August 15,1955.
A. Inspection.
1. Attach angles. Inspect wing attaching 41-47-1 D ouglas Was Service Note 3 of angles, part numbered 570602-20 and -21, for AD-618-3 and Service Note 3 o f AD cracks between the attaching bolt holes.
699-3
The inspection should be conducted with at Each time a control surface is overhauled least a four power magnifying glass at eaCh or repaired, the surface should be rebal periodic inspection not to exceed 450 hours anced. Douglas Service Bulletin No. 207 con flight time.
A more detailed inspection tains instructions on rebalancing.
should be made at the time of removal of the wings for the wing doubler inspection 43-7-1 F airchild Was Service Note 2 of AD-724-2
specified below. All paint should be removed At each periodic inspection, examine the from the angles at that time to permit ex amination with a high power magnifying wing center-section front and rear spars for wood deterioration and weakened glue joints glass.
2. Wing doublers. Inspect the wing at due to moisture accumulation. Method of tach angle doublers for cracks along the bent inspection and repair, if necessary, are cov up flange portion at the wing attachment ered in Fairchild Service Maintenance Bul join t at the following intervals of wing dou letin 45-62-1 dated March 10, 1945, which has been reproduced for CAA personnel.
bler tim e:
a On aircraft having less than 8,000 43- 12-1 D ouglas W as Service N ote 4 o f hours doubler flight time; inspect at 8,000
AD-669-3
hours, or less, and at intervals not to exceed At each periodic inspection, check the 4.000 hours thereafter.
elevator hinge brackets and if cracks are b On aircraft having more than 8,000 present the brackets should be replaced.
hours doubler flight time; where doublers Due to the possibility of vibration causing have not been inspected during the last 4,000 fatigue failures, continuous operation of the hours, such doublers should be inspected im airplanes in the range of engine speeds be mediately and intervals should not exceed tween 1,300 and 1,600 r. p. m. should be 4.000 hours thereafter. Where doublers have avoided. A minimum engine speed of 1,700
been inspected during the last 4,000 hours, r. p. m. during cruising flight is recom inspection should be made at the next 4,000mended. Douglas Service Letter dated Jan hour period and at intervals not to exceed uary 15, 1943, covers this same subject.
4.000 hours thereafter.

507.2 Definitions. Unless otherwise specified herein, all words and phrases defined in P a rt 1 of the Civil A ir R egu lations shall have the same m eaning when used in this part.

507.1 Basis and purpose a Basis.
The basis of this part is 1.24 of the Civil Air Regulations.
b
Purpose.
The purpose of this The wings should be completely removed Part is to providé notice to aircraft oper to permit thorough cleaning of the doublers and inspection with a high power glass.
ators when, as a result of service expe Dy-Chek may be used in lieu of a high rience, an unsafe condition is discovered power glass in conducting the inspection.
in a product; and to prescribe the con 3. Center section line in outer wing jo in t.
ditions and limitations, including inspec Inspection and rework should be made in ac tions, under which the product m ay be cordance with the procedures outlined in A. D. Note 52-22-3.
operated.

44- 20-2 B oeing Was Service Note 1 of AD-719-1 and Service Note 1 o f AD720-1
Inspect by visual means all square alu minum alloy 24SRT tubing for cracks in the following locations: wing spars, front spar fuselage bulkhead, rear spar fuselage bulk head, and fin and stabilizer attachment